The Project Gutenberg eBook of Learning to fly in the U.S. Army
This ebook is for the use of anyone anywhere in the United States and
most other parts of the world at no cost and with almost no restrictions
whatsoever. You may copy it, give it away or re-use it under the terms
of the Project Gutenberg License included with this ebook or online
at www.gutenberg.org. If you are not located in the United States,
you will have to check the laws of the country where you are located
before using this eBook.
Title: Learning to fly in the U.S. Army
a manual of aviation practice
Author: Elisha Noel Fales
Release date: February 8, 2024 [eBook #72902]
Language: English
Original publication: New York: McGraw-Hill Book Company, 1917
Credits: Bob Taylor, Gísli Valgeirsson and the Online Distributed Proofreading Team at https://www.pgdp.net (This file was produced from images generously made available by The Internet Archive)
*** START OF THE PROJECT GUTENBERG EBOOK LEARNING TO FLY IN THE U.S. ARMY ***
Transcriber’s Note
Italic text displayed as: _italic_
Bold text displayed as: =bold=
LEARNING TO FLY
IN THE
U. S. ARMY
_McGraw-Hill Book Co. Inc._
PUBLISHERS OF BOOKS FOR
Coal Age [Illustration: Decoration] Electric Railway Journal
Electrical World [Illustration: Decoration] Engineering News-Record
American Machinist [Illustration: Decoration] The Contractor
Engineering & Mining Journal [Illustration: Decoration] Power
Metallurgical & Chemical Engineering
Electrical Merchandising
[Illustration: A GROUP OF U.S. ARMY STUDENT AVIATORS.
_Frontispiece_
]
LEARNING TO FLY
IN THE
U. S. ARMY
A MANUAL OF AVIATION
PRACTICE
BY
E. N. FALES
FORMERLY ASSISTANT PROFESSOR OF MECHANICAL ENGINEERING
CHAIR OF AERONAUTICS, UNIVERSITY OF ILLINOIS
FIRST EDITION
SECOND IMPRESSION
McGRAW-HILL BOOK COMPANY, INC.
239 WEST 39TH STREET. NEW YORK
LONDON: HILL PUBLISHING CO., LTD.
6 & 8 BOUVERIE ST., E. C.
1917
COPYRIGHT, 1917, BY THE
MCGRAW-HILL BOOK COMPANY, INC.
THE MAPLE PRESS YORK PA
PREFACE
This book is primarily intended for non-technical readers; and for the
student aviators who, called from non-technical occupations, must cram
themselves at short notice with the gist of airplane flying; and who
must omit everything except the outstanding fundamentals.
The desired essentials are here given without sacrificing accuracy
to brevity. It has been necessary to omit many technical details of
interest to the aeronautical engineer, to whose needs other larger
textbooks are adapted as a complete survey of technical aeronautics. In
brief, the book presents the main principles of aviation, such as the
aviator must know in order properly to understand his airplane, keep
it trued up, and operate it in cross-country flights as well as at the
flying field.
Out of the 2000 aeronautical books now in existence, a few are adapted
to use as textbooks for the present need, but none give the particular
and abridged information in tabloid form such as must be adopted for
the best time economy of these students.
It is by the kind permission of Professor E. A. Holbrook, Mr. O. S.
Beyer, and Mr. C. M. Hebbert that chapters VI to XI have been included.
Acknowledgment and full credit is due them as co-authors. Chap. VI,
VII, and part of Chap. XI were prepared by Prof. E. A. Holbrook; Chap.
IX, X, pages 152-157 of Chap. VIII, and pages 173-177 of Chap. XI were
prepared by Mr. O. S. Beyer; Chap. VIII, pages 133-152, was prepared by
Mr. C. M. Hebbert.
In the Chapter on “History of Aviation” only those experiments are
treated which have a bearing on flight today; this chapter is to
be used in conjunction with the Chapter on “Principles of Flight,”
especially as regards controlling the airplane.
The question of Airplane Motors has not been touched, because to do
it justice would unduly increase the size of this volume, and because
adequate treatises on the subject are available.
_Dec._ 12th, 1917.
CONTENTS
PAGE
PREFACE vii
CHAPTER
I. History of Aviation 1
II. Types of Military Airplanes and Uses 18
III. Principles of Flight 39
IV. Flying the Airplane 80
V. Cross-country Flying 89
VI. The Rigging of Airplanes—Nomenclature 113
VII. Materials of Construction 120
VIII. Erecting Airplanes 133
IX. Truing up the Fuselage 158
X. Handling of Airplanes in the Field and at the Bases
Previous to and After Flights 166
XI. Inspection of Airplanes 173
LEARNING TO FLY
IN THE
U. S. ARMY
A MANUAL OF AVIATION
PRACTICE
CHAPTER I
HISTORY OF AVIATION
That part of the history of Aviation which has especial interest for
aviators is of recent date, and extends back only two dozen years. Of
course efforts have been made toward manflight ever since the early
sixteenth century, when Leonardo da Vinci invented the parachute and
became the first patron of aeronautics; between the time of this famous
artist and the present many experimenters have given their attention
to the problem, but previous to the last decade of the nineteenth
century nothing practical was achieved. Then, with the perfection of
the steam engine and the development of the gasoline engine, there came
inducement to sound experimentation, bringing forth such well-known
figures as Maxim, Langley, Lillienthal and Chanute.
The work of each of these men is an interesting story by itself,
especially that of Langley, who approached the matter from a strictly
scientific viewpoint, established testing apparatus and built
successful self-propelled steam models years before the Wright brothers
reported their independent successes. He reproduced his models to full
scale with every expectation of success, but failed, due to exhaustion
of his capital.
=Langley’s Experiments in Aerial Navigation.=—In all the history of
aerial navigation one of the most romantic stories is that describing
the scientific researches begun in 1887 by Langley and culminating in
1896 in the first really successful case of mechanical flight using a
prime mover; continuing up to 1903 when this first successful machine,
a model of 12-ft. span, was reproduced to full scale and manned for
its trial flight by a human pilot; and ending with the destruction of
this full-sized machine on launching, so that Langley missed the glory
of being the actual discoverer of manflight only by a hair’s breadth,
dying shortly afterward of a broken heart, as is conceded by those who
knew him. If this full-scale machine had performed as successfully in
1903 as it actually did after being rebuilt and partly remodelled a
decade later by the Curtiss company, Langley would have antedated the
first successful flight made by the Wright brothers by a narrow margin
of about 2 months.
[Illustration:
(_Courtesy S. S. McClure Co._)
FIG. 1.—The Langley steam model flying machine.
It flew a mile in 1896, the first successful airplane to fly with a
prime mover.]
=Lillienthal (Germany, 1894).=—But omitting details regarding the
early experimenters we will consider only that part of the history of
aviation most important to the prospective aviator. We will confine
ourselves to the sequence of gliding and power experiments begun by
Lillienthal, carried forward by Chanute and brought to completion by
the Wrights.
[Illustration:
(_Courtesy Jas. Means’ “Aeronautical Annual.”_)
FIG. 2.—Lillienthal’s biplane glider in flight, 1894.
Note.—(_a_) Arched wings; (_b_) fixed tail; (_c_) method of balancing
by swinging legs.]
[Illustration: (_Courtesy Jas. Means’ “Aeronautical Annual.”_)
FIG. 3.—Chanute’s biplane glider, 1896.
Note improvement in rigidity by bridge-type trussing.]
Lillienthal was the first man to accomplish successful flights
through the air by the use of artificial wing surfaces. After many
years of experiment and study of soaring birds he constructed rigid
wings which he held to his shoulders and which, after he had gained
considerable velocity by running forward downhill, would catch the air
and lift his weight completely off the ground. The wings were arched,
for he observed this was the case in all birds; flat wings proved
useless in flight, and suggested a reason for the failure of previous
experimenters. To these rigid wings Lillienthal fastened a rigid
tail; the wings and the tail comprised his “glider.” There were no
control levers and the only way the operator could steer was to shift
the balance by swinging his legs one way or the other. Lillienthal
constructed an artificial hill for his gliding so that he could coast
downward for some distance without striking the ground and he was able
to accomplish many glides of a couple of hundred yards in length.
=Chanute (Chicago, 1896).=—Chanute’s experiments in gliding were
quite similar to Lillienthal’s and were made on the sand dunes along
Lake Michigan outside of Chicago. His apparatus was more strongly
constructed, being of trussed biplane type, a construction suggested to
him by his experience in bridge building, and one which persists today
as the basis of strength in our present military biplanes.
=The Wright Brothers, 1901.=—Lillienthal was killed in a glide, having
lost control of his apparatus while some distance above the ground. The
Wright brothers read of his death and commenced thinking over the whole
problem. Lillienthal’s method of balancing his large apparatus by the
mere effect of swinging his legs appeared to them as a very inadequate
means of control. They came to the conclusion that the immediate
problem in artificial flight was the problem of stability, which they
felt should be solved by an entirely different means than that employed
by Lillienthal and Chanute. The work already done had demonstrated
without question that support in the air had been established; with
the addition of controllability the Wrights looked forward to doing
something worth while in the way of artificial flight.
To improve Lillienthal’s method of shifting the weight, they conceived
the idea of leaving the pilot in an immovable position in the glider,
and instead of obliging him to shift his weight this way and that, they
proposed to manipulate the surfaces of the wings themselves by means of
levers under the pilot’s control, so that the same result of balancing
could be obtained by quite a different and superior method.
They set out, therefore, deliberately to solve the whole question of
airplane stability. There was the fore and aft or horizontal stability,
for which Lillienthal had swung his legs forward and backward; there
was in addition the sidewise or lateral stability for which Lillienthal
had swung his legs to left and right. The fundamental requirements
to be met were that during flight the glider should be kept in its
proper attitude without diving or rearing up, and without rolling into
an attitude where one wing tip was higher than the other, i.e., the
machine was to be kept level in both directions.
[Illustration: First Wright glider.
With front elevator, shown flying empty as a kite.
Final Wright glider.
With rudder and elevator. Note right wing warped downward to raise
right wing tip.
A successful downhill glide. Pilot lies prone on bottom wing.
FIG. 4.]
=Fore and Aft Control.=—After some preliminary trials the Wrights
found that the fore and aft balance could be controlled by an elevator
or horizontal rudder, supported on outriggers on the front of the
airplane, and operated by a lever. If the pilot found the glider
pitching too much downward, and tending toward a dive, he would tilt
the elevator upward by moving the lever, thus turning the glider back
into its proper attitude. This elevator in modern machines is back of
the airplane, a better place for it than was chosen by the Wrights.
It may be said that their chief reason for first putting it in front
was that they could see it there and observe its effect. They soon
realized that the rear location gave easier control, and they acted
accordingly.
=Lateral Control.=—After satisfying themselves regarding fore and aft
control, the Wrights took up lateral control. Their problem was to
devise a means for keeping the span of the wings level so that when for
any reason one wing tip should sink lower than the other, it could be
at once raised back to its proper position. Lillienthal had tried to
do this by swinging his legs toward the high side; the shifted weight
restoring the position. The Wrights, to obviate this inadequate method,
bethought themselves to restore equilibrium by means of the wind itself
rather than by gravity. They observed an interesting maneuver employed
by a pigeon which seemed to secure its lateral balance in exactly
the way they wanted; this bird was seen to give its two wings each a
different angle of attack, whereat one wing would lift more forcibly
than the other, thereby rotating the bird bodily in any desired amount
or direction about the line of flight as an axis. To copy this bird
apparatus in a Wright glider, it was found sufficient to alter the
angle of the wing tips only, leaving the chief part of the supporting
surface in its original rigid position. In other words, the wing tips
were to be warped; the one to present greater angle of attack, the
other less angle, exactly as in the case of the pigeon. Suppose the
airplane to develop a list to the left, the wing on that side sinking,
the pilot was to increase the angle at the tip of this left-hand wing
by moving the warping lever, and at the same time decrease the angle
of the right-hand wing by the same lever. He was to hold this position
until the airplane was righted and brought back to level position.
This arrangement proved to have the effect anticipated and maintained
stability easily on a glider much larger than Lillienthal ever managed
with his leg-swinging method.
=Directional Control.=—We have now followed the development by the
Wrights of airplane control as regards:
1. Fore and aft or “pitching” motion, accomplished by an elevator
operated by lever.
2. Lateral or “rolling” motion accomplished by wing warping operated by
a second lever.
These were the only controls used in the earliest gliders. It remains
to consider the third element of control, viz:
3. The directional or “yawing” control, which is accomplished by an
ordinary vertical rudder operated by a third lever.
The Wrights found the warping had all the effect anticipated but had
also certain secondary and undesirable effects. Whenever they applied
the warping lever to correct the rolling motion, the glider responded
as far as rolling control was concerned, but at the same time would
“yaw” or swerve out of its course to right or left. This was a serious
complication. For, in the moment of swerving, the high wing which they
desired to depress would advance faster than the low wing, and solely
by its higher velocity tended to develop a greater lift and thereby
neutralize the beneficial effect of the warp. In many of their early
glides, because of pronounced swerving, the warp effect was entirely
counteracted and failed to bring the glider back to level; with the
result that one wing tip would sink, at the same time swinging backward
until the machine was brought to the ground. No amount of controlling
could prevent this.
After much bewilderment on this point, the Wrights observed that
whenever a wing tip was warped to a large angle its resistance became
relatively greater and it slowed up while the opposite side went ahead.
They at once hit upon the idea of a rudder, previously considered
unnecessary, which they believed could be turned in each case of
yawing just enough to create a new and apposing yawing force of equal
magnitude.
They therefore attached a rudder at the rear, connecting its tiller
ropes to lever No. 2, and giving this lever a compound motion so that
one hand could operate either warp or rudder control independently (or
simultaneously in proper proportion to eliminate the yawing tendency
above mentioned). This combination is the basis of the Wright patents
and is essential in airplanes of today.
Great success now ensued in their gliding experiments; the machine was
always in perfect control; could be manipulated in any desired manner;
turned to right or left, or brought down to earth with safety.
Thus were the three elements of control applied by the Wrights to their
glider and the problem apparent in Lillienthal’s death was solved.
The next step was to install a power plant able to maintain forward
speed without resorting to coasting downhill by gravity; and therefore
capable of producing a horizontal flight.
In developing a power flyer aside from the question of control the
proper design was arrived at as follows:
=Efficiency of Wings.=—The Wrights knew from Langley and Chanute that
flat wings were inefficient and useless, and curved wings essential;
they did not know whether the amount of curvature mattered much. To
find this out by trials in gliding would be slow and expensive. They
adopted a better way—the wind-tunnel method, wherein small-scale models
were tested and compared for efficiency in a blast of air. They made
their wind tunnel 16 in. in diameter and created a powerful air blast
through it by means of an engine-driven fan. Small models of wings
were placed in the center of this confined air blast, mounted on a
balance arm which projected into the tunnel from the outside. The
air forces and efficiency of the models were thus measured. A large
variety of shapes were tested and one was selected as best of all from
the standpoint of curvature and rounded wing tips. This shape was
adopted in their flyer, and though on a much larger scale fulfilled
the predictions made for its efficiency in the indoor wind-tunnel
experiments.
The Wright glider was, of course, a biplane model. They tested a small
6-in. model biplane and found that the two wings together were less
efficient than either wing by itself. However, other considerations,
such as rigidity of trussing, decided them to adopt the biplane rather
than a monoplane arrangement.
=Low Resistance to Forward Motion.=—The Wrights used their wind tunnel
also in choosing for the struts of their airplane a shape which would
present least head resistance to forward motion. They found that a
square strut had a resistance which could be decreased by changing
the shape to resemble a fish. The resistance of the pilot himself was
decreased by making him lie prone, face downward on the bottom wing.
=Propeller Efficiency.=—Although little data on the subject of
propeller efficiency was available to the Wrights, they were able to
arrive at a very creditable design wherein two propellers were used,
driven from a single motor, and rotating one each side of the pilot.
The mechanical difficulties which have since embarrassed the use of two
propellers were less with the Wrights because they were dealing with
smaller horsepowers than are in use today; they therefore were able to
realize a very high propeller efficiency.
=Motor.=—When the Wrights were ready to apply a motor to their glider,
they found it impossible to secure one light enough, and had to set
about building one themselves. They adopted a four-cylinder type,
water-cooled, and their aim was to save weight and complication
wherever possible. Their first motor gave about 12 hp., which was
raised to a higher and higher figure by subsequent improvements until
it reached 20 hp. In its earliest stages it was able to give sufficient
power for short horizontal flights.
=Means of Starting and Landing.=—One reason the Wrights could use such
low horsepower was that they employed auxiliary starting apparatus to
get up original speed. They knew that less horsepower was necessary to
fly an airplane after it was once in the air than was necessary to get
it into the air at the start, and they therefore rigged up a catapult
which projected their airplane forward on a rolling carriage with great
force at the start, so that all the motor had to do was to maintain
the flight in air. The Wright airplane had at first no landing wheels,
and was provided only with light skids on which it could make a decent
landing. Present-day airplanes, of course, have wheels on which to roll
both at starting and at landing and their motors are powerful enough to
eliminate the necessity for a starting catapult.
[Illustration: (_Courtesy American Technical Society and Scientific American
Supplement._)
FIG. 5.—Details of Bleriot XI monoplane.]
=Bleriot’s Contribution to Aviation.=—Bleriot experimented a great
many years before he attained success and did so years after the
Wrights had successfully flown. But when he did obtain success, his
great ingenuity produced features of design which were a decided step
forward. He added a body to the airplane and produced a machine which
instead of being a pair of wings with various appendages, was a body
to which wings were attached, giving a more shipshape and convenient
arrangement. The motor, instead of being located beside the pilot as
in the Wright machine, was put in the very front of the body ahead of
the pilot where it was not likely to fall on him in case of a smash.
This location of the motor entailed the use of a single propeller at
the front, a “tractor” screw as it was called, less efficient than the
double propeller of the Wrights, but better from the standpoint of
mechanical convenience. The body of a Bleriot, which was quite similar
to the body of any bird in its general arrangement, projected to the
rear in a tapering form and carried at the rear a rudder and elevator.
The motor, pilot and tanks were thus enclosed within the body and away
from the wind. Bleriot’s contributions were then, better location of
the motor, adaptation of the body or “fuselage,” elimination of the
front elevator and substitution of the rear elevator.
=Nieuport and Fokker’s Contribution to Aviation.=—A further advance
on Bleriot’s design was made by Nieuport and later by Fokker. The
former utilized the fuselage principle of Bleriot and enclosed the
whole framework, front and back, to give a stream-line form, and even
went so far as to make wind-tunnel experiments from which he was able
to choose a very efficient fuselage shape as well as wing and strut
efficiency.
[Illustration:
(_From Hayward’s “Practical Aeronautics.”_)
FIG. 6.—Nieuport monoplane.
Representing an advance in speed, due to covered stream-line body.]
CHAPTER II
TYPES OF MILITARY AIRPLANES AND THEIR USES
=Modern Airplanes Combining Best Features of Previous Experiments.=—The
modern airplane, of which the Curtiss training machine used at the U.
S. Aviation Schools is typical, is a combination of the best features
referred to above. It is of the biplane type for, as shown by Chanute,
rigid trussing is thus possible, an advantage sufficient to offset the
slight loss of efficiency which exists in the biplane. The landing gear
consists of two wheels provided with shock absorbers; the body is of
the general stream-line type, enclosed from front to back, containing
comfortable seats for the passengers and enclosing the motor and tanks
away from the wind. The motor is at the front where, in an accident,
it will not be on top of the pilot. The warping effect is obtained by
hinging flaps at the wing tips, the same effect being obtained while at
the same time leaving the whole wing structure rigid and strong rather
than flexible and weak, as was the case in the early warping type of
machines.
=Military Airplanes of Today.=—In the modern airplane, therefore,
we see that matters of efficiency, to which the Wrights gave great
attention, have been sacrificed in favor of convenience, particularly
in favor of power and speed. This is the effect of military demands
for airplanes where power, speed, and ability to climb fast are vital
requirements. To escape from or to destroy an enemy, high speed and
ability to climb fast are, of course, prerequisites. Moreover, from the
standpoint of safety in maneuvering it is desirable to have a reserve
of power and speed. Therefore, the design of military machines has
tended in a given direction up to the present.
New considerations have arisen on this account, such as for instance
the question of landing. Fast machines in general make high-speed
landings, and are for that reason dangerous. The original Wright
machines were built to land at such a slow speed that ordinary skids
were sufficient to take the shocks. Nowadays the high-powered airplane
is likely to come to grief in landing more than at any other time.
The question of stability in flight has of recent years been treated
mathematically and experimentally, using of course the fundamental
system of “three axes control” first applied by the Wrights. It has
been found that by properly proportioning the tail surfaces and
properly arranging the wings and center of gravity, any desired degree
of stability may be obtained, such that a machine may be made almost
self-flying or, if preferred, may be made very sensitive.
All of the above features of design have had consideration in the
latest types of military airplanes. Observe the high speed of the
latest speed scouts, where power is concentrated exclusively on speed
and climbing ability and landing speed is dangerously high. We see
the advent of the triplane scout, which is an attempt to secure slow
landing speed combined with high flying speed. We see machines with the
motor and propeller in the rear, or with two motors, one to each side
of the body out in the wings, the object being to avoid interference of
the propeller with the range of gun fire. In short, we see the effect
of many military considerations on the design of the airplane. It will
be interesting at this point to survey what are these military uses of
the airplane.
=Aerial Fighting.=—Fighting in the air is the most spectacular use
to which military airplanes have been put. The first requirements in
a fighting airplane are speed and climbing ability and these must be
obtained at all costs, because speed and climb are weapons of defense
and offense second only in value to the gun itself. The concentration
of motive power for speed and climb requires that as little weight as
possible be used; and therefore the fastest fighters are designed to
carry only one person and are very light and of course very small.
It is usual to have one gun fixed to the body and firing through the
propeller in the case of a tractor, and a second adjustable aim gun
pointing upwards over the top wing. This gives the pilot a chance to
fire a round at the enemy while “sitting on his tail” or following
from behind; and then when diving below the enemy the second gun is
available for shooting overhead. These very high-speed fighters are
difficult to land, due to their speed, and are suitable only for the
highest-trained pilots.
=Directing Artillery Fire.=—The friendly airplane is sent out over
the enemy’s positions, soars above the target, sends back signals
by wireless to the friendly battery regarding the effect of fire;
practically dictating the success of artillery operations.
=Reconnaissance.=—The friendly airplanes go out, usually in squads for
the sake of protection, and observe by means of photographs or vision
size of enemy troops, batteries, trenches, lines of communication,
etc.; report the situation to headquarters as a source of daily
photographic record of the operations of the enemy, to such an extent
that any change of the enemy’s position can be analyzed. Of course the
value of reconnaissance is lessened when the enemy disguises his gun
emplacements, etc. In reconnaissance machines it is important to have
two persons, one to steer and the other to scan the countryside. The
reconnaissance machine is therefore a two-place type which may or may
not have armament. It need not be so fast, especially when convoyed by
fighting speed scouts. The two-place machines are frequently used for
fighting, in which case the pilot will have a gun fixed to the body and
shooting through the propeller, and the passenger, especially in German
machines, will also have a gun mounted in the turret so that it may be
shot in a variety of directions by the passenger.
=Bomb Dropping.=—This maneuver requires squad flights to be of great
value. The fundamental characteristic of a bombing airplane is its
ability to carry great weight. Such machines are of comparatively
large size and not particularly fast. Weight carrying is of course
incompatible with speed and climbing ability and therefore the bombing
machine must be a compromise if it is to have any reasonable speed.
It may be said that airplanes compare very unfavorably with dirigible
balloons for bomb raids because the latter are able to carry several
tons of bombs as against the airplane’s quarter of a ton.
=Locating Submarines.=—For coast patrol or submarine spotting, the
airplane is an important factor, for from an airplane it is possible
to see for a considerable depth into the water, and to locate hostile
submarines.
=Training Student Aviators.=—The training machine on which prospective
aviators secure their flying instruction may be considered as a
type in which great speed and power is not essential, but in which
reliability and ease of control is desirable. The typical military
training airplane in this country is a single-motor tractor of
moderate horsepower (about 100) having of course the seats in tandem
and furnished with dual control so that operation may be from either
pilot’s or passenger’s seat. The dual-control system of training which
prevails in this country differs from the French method of starting
the pupil out alone to try his wings; it enables the pilot to keep
a constant eye upon the pupil’s control manipulations and to correct
them instantly whenever they are in error before any damage is done.
A possible improvement in the dual-control training machine will be
the substitution of side by side seats for tandem seats. At present,
communication is difficult due to the great noise of the motor; but
with the adoption of side by side seats such as is used in naval
training schools, the pilot and pupil will be able to communicate to
better advantage.
[Illustration: FIG. 7.—U. S. training airplane, dual control (Curtiss
JN-4).
Speed 43 to 72 mi. per hr.; climbing ability 300 ft. per min.; 90 h.p.;
weight fully loaded 1,890 lbs.]
=Types of Airplanes.=—To suit the foregoing purposes flying machines
exist in seven distinct different shapes at the present time, namely:
monoplanes, biplanes, triplanes, single-motor tractors, single-motor
pushers, double-motor machines and marine airplanes. The last four
types may be either monoplanes, biplanes or triplanes. In order to
understand the adoption of one or the other type for military use, it
is well to run over the characteristics of the seven types mentioned.
=Monoplanes.=—The simplest form of airplane is the monoplane which
is fashioned after the manner of a bird (see Fig. 34). There are two
things to say in favor of the monoplane: first, that the passengers
have an unobstructed view forward and range of gun fire upward because
there is no wing above them; second, the aerodynamic efficiency of
the monoplane is superior to any other type. But when the bird design
is applied to a man-carrying apparatus, it becomes impracticable
to construct spars to take the place of the bird’s wing bones; and
therefore to give the wings proper strength it becomes necessary to
truss them with numerous tension wires stretching from the running gear
out to various portions of the wings. There are also wires running
from a vertical mast above the body to a point on the top part of the
wing; these wires, while they give the wing no added strength during
a flight, are necessary in order that the shock of landing shall not
break the wings off sharp at the shoulder. It is characteristic of
monoplane construction that from a point below the body and also from
a point above the body a number of heavy wires run outward to various
points on the wings; and it may be said that the strength to be secured
from this construction is not all that could be desired.
=Biplanes.=—The biplane is an improvement over the monoplane from the
latter standpoint; in the biplane there are two parallel surfaces
separated by vertical sticks or struts, thus forming parallelograms
which are susceptible of being trussed by means of tension-wire
diagonals in a manner familiar and well understood in case of bridges.
It is possible to build up biplane wings of great rigidity and strength
by this system, much more easily than in case of monoplanes. However,
the biplane type is from the standpoint of efficiency inferior to the
monoplane. This is due to the fact that the vacuum above the bottom
wing which is so necessary for high duty is somewhat interfered with
by the upper wing; thus while in a biplane the upper wing operates
about as efficiently as it would operate in a monoplane, yet the lower
wing has its efficiency materially reduced and the resulting overall
efficiency of a biplane compared area for area with the monoplane
is about 85 per cent. as great. However, recent developments of the
airplane have more or less put efficiency in the background and as
a result today the biplane is more popular than the monoplane. In
addition to the greater strength of biplane wings their span may be
less than the monoplane for the same supporting area. This makes them
less unwieldy. Moreover, for certain reasons a biplane machine of high
speed may be landed at a lower speed than equivalent monoplanes.
=Triplanes.=—What is true of the biplane is more true in almost every
item of the triplane, that is, it is comparatively strong, compact, and
of low landing speed, but of reduced efficiency.
[Illustration: FIG. 8.—U. S. speed scout triplane, single seater.
(Curtiss Model S3), 55 to 115 mi. per hr.; climbing ability 900 ft. per
min.; 100 h.p.; weight fully loaded 1,320 lbs.]
=Single-Motor Tractors=.—The single-motor tractor received its name
simply because the propeller is in front and draws the machine forward;
but this location of the propeller necessitates a distinct type of
airplane, wherein the power plant is located at the very nose of the
machine. The tractor type has the pilot and passenger located in or
to the rear of the wings in order that their weight may balance the
weight of the motor. This means that the view and range of fire of
the passengers is obstructed in a forward direction by the wings, and
in machines such as the U. S. training machine, the passenger, who is
practically in the center of the wings, can not look directly upward
nor directly downward. Moreover, as concerns gun fire, the propeller
of a tractor obstructs the range straight ahead. In the tractor the
tail is supported at the rear and on the same body which contains the
motor and passengers; this body constitutes a stream-line housing for
the machinery, seats, etc., and therefore has low wind resistance.
The tractor is a very shipshape design, compact and simple and is
at present the prevailing type on the European war front. However,
it has disadvantages which are only overcome in other types. One of
these disadvantages is of course the obstruction to range of gun fire.
The present practice in fighting airplanes is simply to shoot the
gun straight through the circle of rotation of the propeller on the
assumption that most of the bullets will get through and that those
which hit the shank of the propeller blade will be deflected by proper
armoring. An attempt is made to insure that all the shots will get
through by connecting the gun mechanism mechanically to the motor shaft
in such a way that bullets will be discharged only at the instant
when their path is unobstructed by a propeller blade. This practice
is possible of course only in guns which are fixed immovably to the
airplane.
[Illustration: FIG. 9.—Fuselage diagram, Curtiss “R4” reconnaissance
biplane.
Speed 48 to 90 mi. per hr.; climbing ability 400 ft. per min.; 200
h.p.; weight fully loaded 3,245 lbs.]
[Illustration: FIG. 10.—An American pusher biplane design.
Crew in front, motor and propeller in the rear, tail support on
outriggers.]
=Single-motor Pusher Airplanes.=—The pusher type has popularity because
the propeller and motor rotate to the rear of the passenger, who takes
his place in the very front of the body and has an open range of vision
and gun fire downward, upward and sideways. Another point in favor of
the pusher is that the oil and fumes of the motor do not blow into his
face as in the case of the tractor. The disadvantage of the pusher is
that the motor, being located behind the pilot, will be on top of him
in the case of a fall. Another disadvantage is that the body can not
be given its shipshape stream-line form because to do so will interfere
with the rotation of the propeller. Therefore, the body is abruptly
terminated just to the rear of the wings and it is just long enough to
hold the passenger and the motor, the propeller sticking out behind.
The tail surfaces are then attached to the airplane by means of long
outriggers springing from the wing beams at points sufficiently far
from the propeller axis so as not to interfere with the propeller.
[Illustration: FIG. 11.—U. S. army battle plane.
Two 100 h.p. motors; speed 85 mi. per hr.]
=Double-motor Machines.=—In order to combine the advantages of the
tractor and pusher types and eliminate their disadvantages, the
double-motor machines have been developed. In these there is no
machinery whatever in the body either in front or back, and the
passengers may take seats at the extreme front as is desirable. The
body then tapers off to the rear in stream-line form and supports the
tail surfaces. The power plants are in duplicate and one is located
to each side of the body out on the wings. It is customary to enclose
each of these two motors in a casing so that the whole power plant
presents a more or less stream-line shape to the wind, the propellers
projecting from the front or rear of these stream-line shapes. It
may be said that in the double-motor airplane it makes very little
difference whether the propeller is in front or behind so that while a
“twin-motor” machine may be more accurately specified as a “twin-motor
pusher” or a “twin-motor tractor,” it is usually sufficient indication
of a machine’s characteristics to call it a twin-motor machine.
By adopting this twin-motor form we bring in new disadvantages. One of
these is due to the fact that the heavy motors are now located some
distance from the center of gravity of the machine. This requires
stronger supporting members between the motor and the body. It also
makes the lateral control comparatively logy for now the heavy masses
are far from the center of gravity, resisting the pilot’s efforts to
use the lateral control. The second disadvantage in the twin-motor
type results from possible stoppage of either motor. In this case, of
course, the propelling force is some distance off center and is also
reduced to one-half its value requiring energetic exercise of the
control wheel to maintain equilibrium. It is reported, however, that
twin machines can continue to fly and even climb with only one motor
running. In this country the twin-motor type has not developed as was
hoped at first, and on the European firing lines it is not so numerous
as the single-motor tractor type.
=Marine Airplanes=.—The possibility of mechanical flight having once
been established and wheels having been applied to the airplane so that
it could start from and land on the ground, the logical next step was
to substitute some form of boat for the wheels so that flights could be
made over the water.
Experiments were made in France by M. Fabre in this direction and in
this country by G. H. Curtiss. The latter, in his flight down the
Hudson from Albany to New York, equipped his airplane with a light
float to provide against forced landing in the river. Pursuing this
general idea he made some experiments under the auspices of Alexander
Graham Bell’s Aerial Experiment Association, in which a canoe was
substituted for the wheels, and in which an attempt was made to start
from the surface of the water. Success did not come at first and this
plan gave no satisfaction. Curtiss next turned his attention to the
hydroplane type of boat and made a series of experiments at San Diego.
The hydroplane appeared to be much better adapted to his purpose than
the canoe had been, and he was able to obtain success.
[Illustration: FIG. 12.—Thomas Type H. S. seaplane. Double pontoons.
Speed 47 to 82 mi. per hr.; climbing ability 270 ft. per min.; 135
h.p.; weight, fully loaded 2,600 lbs.]
[Illustration: FIG. 13.—Curtiss Model F flying boat.
Speed 45 to 65 mi. per hr.; climbing ability 150 ft. per min.; 90 h.p.;
weight fully loaded 2,100 lbs.]
=The Hydro-airplane (or “Seaplane”).=—From analogy to the airplane one
might at first imagine that a suitable hydroplane would have a wide
span and fore and aft length; but such proportion would give a very
poor stability on the water, and would require auxiliary hydroplanes
in the same way that an airplane requires auxiliary guiding surfaces.
So Curtiss, with his customary eye for simplicity and convenience,
adopted a type of hydroplane which had the general proportions of
an ordinary boat, _i.e._, was long and narrow, thus obviating the
necessity of auxiliary hydroplanes at the tail of the machine. To
prevent the machine’s tipping over sidewise, “wing pontoons” were
attached at the lower wing tips to prevent capsizing.
[Illustration: FIG. 14.—Building a flying boat hull.
Note wing stumps and hydroplane fins.]
[Illustration: FIG. 15.—Method of hoisting a marine airplane aboard
ship.]
=The Flying Boat.=—In the early hydro-airplane, which was thus
developed, the motor and pilot were above in the usual position in the
wings, while the hydroplane itself was a considerable distance below
the wings. Thus there was a good deal of head resistance. Curtiss set
about reducing this head resistance as far as possible and tried to
incorporate the pilot’s seat with the hydroplane pontoon. The outcome
of his endeavor was that he developed a boat with a tapering stern.
The pilot, gasoline tanks, etc., are located inside of the hull; the
tapering stern provides a backbone to which the tail surfaces can be
readily attached; the wings fixed to the sides of the hull in a manner
analogous to the wing fastenings of the modern military airplane; and
the motor alone remains exposed to the wind. This is the flying boat;
its action on the water is analogous to the action of the hydroplane
for the bottom of this boat hull is made in hydroplane form; indeed, in
the latest types of flying boat, the hydroplane area is increased by
extending it to right and left of the boat hull. The flying boat is an
ingenious combination, wherein the characteristics of the hydroplane
are combined with the seaworthiness of the ordinary boat, and at the
same time wind resistance is reduced to a minimum.
The hydro-airplane remains in use, however, being preferable to the
flying boat for certain purposes, and often is termed seaplane.
=Future of the Airplane.=—In order to be commercially successful and
have a commercial future after the war, the following weak points in
airplane design must be rectified.
1. _Motor._—Airplane motors are imperfect and unreliable at present and
there must be considerable progress before this type of motor which is
very light and delicate can be considered as reliable or can be made in
large enough quantities to cut down the cost.
2. _Landing._—The necessity of landing at considerable speed, say 40
to 50 miles per hour, requires a wide flat space, such as is not easy
to find, and if the present type of airplane is to become commercially
numerous, a large number of landing fields must be developed all over
the country.
3. _Danger._—The airplane is by no means so dangerous as the public has
been led to think from the exploits of the daredevil circus performers
of the past 10 years; with careful manipulation it will make trips day
after day without any damage. However, it is not a foolproof machine
and there remains an element of danger on this account, which it is
hoped will one day be eliminated.
=Future Uses of the Airplane.=—Future uses of the airplane are many
after the war is over. The postal service of several governments are
considering this means of mail delivery; the sports use as in the
past will continue to flourish; express carrying may be expected
in inaccessible countries where railroads and roads do not give
access and where high-speed delivery by countless airplanes would
aid materially in the development of newly opened countries. For
airplane transportation will require no expensive right-of-way,
rubber-tire renewals, etc. Minor uses of airplanes are on such duties
as forest-fire patrol, working at life-saving stations, etc.
=American Airplane Industries.=—The magnitude of the airplane industry
in this country is great, although not so great as in Europe. Leading
business men have invested in this industry with the firm belief that
it will become a profitable one, irrespective of war. We see a number
of leading bankers and also automobile manufacturers in various parts
of the country putting their money into this new industry. Now that
a great demand has sprung up on our side of the water for airplanes,
we will expect to see this industry increase more rapidly still. The
only result can be, from all the interest and importance attached
to aviation, that after the war is over, large commercial uses will
develop which will offer employment to those who go into the work at
this time for military reasons. No one can predict exactly what turn
the situation will take, but there is every indication that aviation
has graduated from the primary class of experimental work and is to
be considered now as an industry along with the automobile business,
motor-boat business, etc.
CHAPTER III
PRINCIPLES OF FLIGHT
=Support of an Airplane by Its Wings.=—An airplane is supported just
as definitely as though on top of a post, and by the same law, namely
reaction. If you try to sweep the air downward with a wing held at a
slight angle, the air just before it consents to be pushed downward,
delivers a momentary reaction which is upward. If you have a bag of
air in your hand it exerts no push upward of course; but the minute
you give it a quick push downward it resists, due to its inertia, thus
delivering an upward “reaction” against your hand.
Whenever you move anything, it reacts an amount just equal to the force
that is moving it; if you move a bullet out of a gun, just before
starting the bullet reacts and you have “kick.” If you should shoot a
thousand guns downward, the reaction would be considerable, and for the
instant might be sufficient to support heavy weight.
The airplane is a device for pushing downward millions of little
bullets, made out of air and exceedingly small and light. The wing of
an airplane sweeps through these bullets, or molecules, of air like a
horizontal plow, wedges the particles downward in vast numbers and in
a continual stream, making up in amount what is lacking in weight, so
that as long as the airplane rushes along, there are many thousands
of cubic feet of air forced down beneath its wings, delivering up
a reaction that results in complete support for the machine. This
reaction is just as definite and secure as though the machine were
supported from the ground on wheels, but it disappears entirely when
the airplane is at rest. Part of the whir of a training machine as it
glides back to earth is made by the air driven downward from the wings;
the same phenomenon may be noticed when a bat flies close to your ears
at night, and if you were a few feet below the airplane as it flew, you
would feel the rush of air driven downward from its wings (see Fig. 16).
The net result of all the reactive pushes from this air is =lift=. It
may amount to several pounds for every square foot of the wing surface.
This is all that need be said about why the air supports an airplane;
all you have to remember is that as long as you have the forward
sweeping movement, you will have the lift.
The forward movement is absolutely essential, however, and to maintain
it requires a lot of horsepower and gasoline. For it is by means of
the engine and propeller that this forward movement is maintained. The
engine is a device for creating forward movement—the propeller drives
the machine ahead in exactly the same way as is the case in a torpedo,
or steamboat.
[Illustration: FIG. 16.—Relative path of air particles past an airplane.
This diagram illustrates the general downward trend of the stratum of
air met by the wings.]
=Lift.=—Assuming that we have all the forward motion needed, let
us now investigate the lift that results. Experimenters such as
the Wrights and others have found out how to get this lift most
conveniently. Lift depends upon the four following factors:
1. Area. 2. Density of air. 3. Angle of incidence. 4. Speed of motion.
1. _Relation of Area of Wings to Support._—Consider a small wing;
suppose it to be held by hand outside a train window in a given
attitude, its area being 1 sq. ft. It tends to lift a certain amount,
say 5 lb. Now increase its size to 2 sq. ft. and it will lift with
10-lb. force, tending to get away from your grasp. Rule: When only the
area of a wing is changed, its lift varies with the area. If, as above
mentioned, you can get 5 lb. of lift from each square foot of wing
surface, you can by the same sign get 10-lb. of lift from 2 sq. ft. And
if you have 500 sq. ft. of surface you can get 2500 lb. of lift.
[Illustration: FIG. 17.—Diagram showing that in fast airplanes wings
are small; in slow airplanes wings are large.
(Above) Small wings; speed 115 mi. per hr.; for fighting. One seat.
(Below) Large wings; speed 80 mi. per hr.; for reconnaissance. Two
seats.]
Regarding =area= of wing surface, the pilot does not have to worry in
a flight since he can do nothing to change it anyway. All he needs to
know is that in different airplanes small wing area accompanies high
speed and small weight-carrying capacity, as in the case of the Fokker
and Sopwith speed scouts (see Fig. 17). Conversely, large wing areas
are used for heavy load carrying and slow speed (see Fig. 18). Speed
and weight-carrying capacity thus appear to be antagonistic and can not
both be attained with efficiency, but only at the expense of enormous
power. The incompatibility between high speed and weight carrying keeps
the designer busy in efforts toward a reconciliation.
[Illustration: FIG. 18.—Diagram showing use of large wings for heavy
airplanes, and small wings for light airplanes.]
2. _Density._—The second factor affecting the lift is the character of
the air itself. I refer to the density of the air. The heavier each
particle of air becomes, the more reaction it can furnish to the wing
that drives it downward; so on days when the barometer is high the wing
will lift more than on other days. Now the air is heaviest, or most
dense, right near the ground; because in supporting the 50 miles or so
of air above it, it becomes compressed and has more weight per cubic
foot. Therefore, the wing gets more lift at a low altitude than at a
high. Some airplanes will fly when low down but won’t fly at all high
up. In Mexico, for instance, when the punitive expedition started out
they were already at an altitude of several thousand feet above sea
level. The airplanes had been built for use at places like New York and
England, close to sea level, and when our army officers tried to fly
with them in Mexico, they would not fly properly, and the factory had
to redesign them.
Regarding _density_, the pilot should know that for a low density he
should theoretically get a high speed. As density decreases, high up in
the air, the speed tends to increase, and moreover he gets more speed
for the same amount of gasoline. Unfortunately, at an altitude the
motor power falls off, so that nowadays the speed is not faster high up
than low down; but when the motor builders succeed in designing their
motors to give the same horsepower at 20,000 ft. as they do on the
ground, airplanes will be able to reach terrific speed by doing their
work above the clouds.
It is found desirable to give large wings to airplanes which are going
to fly at high altitudes, so as to offset the lack of density by an
increase in area, thus leaving the angle range—that is, the speed
range—as large as possible. The army airplanes in Mexico mentioned
above were simply given a new set of larger wings to offset the lower
air density in Mexico, and thereafter flew better.
3. _Angle of Incidence._—The angle of incidence is defined as the
_angle between the wing-chord and the line of flight_. The line of
flight is the direction of motion of the airplane, and is distinct from
the axis of the airplane which corresponds with the line of flight only
for a single angle of incidence. If the line of flight is horizontal,
the airplane may be flying tail-high, tail-level, or tail-low; that is,
its axis may have varying positions for a given line of flight. This
is true, if the line of flight is inclined, as in climbing. It is a
mistake to confuse the line of flight with the axis of the machine.
The angle of incidence of the wings of the U. S. training machine
may have any value from 15° down. When the angle is smaller the lift
of the wings is smaller. Consider the model wing held out of a train
window; if its front edge is tilted up to an angle of 15° with the line
of motion it will lift say 1 lb.; if reduced to a 10° angle, it will
lift less, say ⅔ lb. A model of the training-machine wing could be
tilted down to an angle several degrees less than zero before its lift
disappeared, because it is a curved, not a flat wing; this angle would
be the “neutral-lift” angle; notice then that O° is not a neutral-lift
angle, and therefore may be used in flight.
If the model wing were tilted up to an angle greater than 15°, the lift
would not increase any more, but would be found to decrease. For this
wing, 15° is called the critical, or “Stalling” angle, beyond which it
is unwise to go.
4. _Velocity._—If the model wing which is imagined to be held out of
the car window, is held now in a fixed position at a given angle of
incidence, any change of the train’s speed will result in a change
of lift; should the speed rise from 30 miles per hour to double this
value, the lift would increase enormously, fourfold in fact.
Lift varies as the square of the speed. Thus any increase or decrease
of speed results in a great increase or decrease of lift.
=Interdependence of Angle of Incidence and Velocity.=—The four factors
above mentioned all contribute to the lift; if in an airplane wing each
factor be given a definite value, the resulting lift is determined
according to the formula:
_L = KrAV^2_
where _L_ is lift.
_K_ is a coefficient referring to the angle.
_A_ is the area.
_V_ is the velocity.
_r_ is the density.
Two only of these quantities change materially in flight, the angle
and the velocity; the lift itself remains substantially the same under
most normal circumstances. The angle always changes simultaneously with
the velocity, increasing when the velocity decreases. Thus the drop of
lift due to velocity decrease is balanced by gain of lift due to angle
increase, and the lift remains unchanged when speed changes.
Speed change then requires that the pilot alter the angle of incidence
simultaneously with the throttle; so there are two things to do, unlike
the case of the automobile where only the throttle is altered.
=Minimum Speed.=—When, in slowing up an airplane, the angle of
incidence reaches the 15° limit, no further decrease of speed is
allowable; therefore, the critical angle determines the minimum limit
of speed. If for any reason the machine exceeds the 15° limit, it must
speed up to gain support; that is, the pilot has to increase angle and
speed simultaneously instead of oppositely.
=Efficiency of Airplane Wings.=—I said at the beginning of this chapter
that the airplane was a device for pushing down an enormous quantity
of air. A certain amount of force has to be furnished in order to
keep the airplane moving, and this force is furnished by the engine
and propeller. The propeller by giving a certain amount of push in a
horizontal direction to the airplane wing enables this wing to extract
from the air ten or twenty times this amount of push in a vertical
direction; that is, the airplane wing will give you 10 lb. or more of
lifting in exchange for 1 lb. of push.
[Illustration: FIG. 19.
Lift and Drift.—Lift is perpendicular to line of flight, drift is
parallel.
Angle of Incidence.—Wing in position shown has angle of 5° if moving
in direction “A,” 10° if in direction “B;” and a negative angle of 4°
if moving in direction “C.” In the last case it is moving along its
neutral-lift-line, lift becomes zero. ]
The propeller push is necessary to overcome the drift or resistance of
the wings to forward motion. It appears then that the airplane wing as
it moves through the air has two forces on it, one acting straight up
and called “lift,” the other acting straight back and called “drift”
(see Fig. 19). The lift is several times greater than the drift, and
the situation is quite analogous to that of a kite, which rises upward
in the air due to its lift but at the same time drifts backward with
the wind due to its drift. In the case of the kite the string takes up
an angle which just balances the joint effect of the lift and drift.
The efficiency of an airplane wing is indicated by the ratio of lift
to drift, and for a given lift, the efficiency is best, therefore, for
small drift. If the lift is 1900 lb. and the wing drift 190 lb.,
Wing efficiency = Lift or weight/Wing drift = 1900/190 = 10
=Factors Determining Best Efficiency.=—It goes without saying that an
airplane wing should attain the best efficiency it can, and there are
several ways of doing this.
The first relates to the question of angle of incidence; we have
already discussed the effect of angle on lift, but when we come to
discuss its effect on efficiency we find that there is only one angle
at which we can get the best efficiency. This is a small angle, about
3° to 6°; at this angle the lift is nowhere near as much as it would be
at 10° or 15°, but the drift is so small compared to the lift that it
is found desirable in airplanes to employ these small angles for normal
flight. As the angle increases above this value of maximum efficiency,
the efficiency drops off, and when you get up to the stalling angle,
the efficiency becomes very low indeed (see Fig. 20).
[Illustration: FIG. 20.—Wing characteristics.
Curves showing lift, drift, efficiency, and center of pressure travel
of typical training-airplane wing, as determined in Aerodynamical
Laboratory.]
The second way to get good efficiency is to choose the shape of the
wings properly. For instance, early experimenters tried to get results
with flat wings, and failed completely, for the flat wing proved to be
very inefficient. When it was observed that birds had curved wings,
this principle was applied to early experiments and then for the
first time man was able to obtain support in a flying machine. The
fundamental principle of efficiency in wings is that they must be
curved, or cambered, as it is sometimes called. This is because as the
wing rushes onward it wants to sweep the air downward smoothly and
without shock, as can be done only when the wing is curved (see air
flow, Fig. 21).
[Illustration: FIG. 21.—Efficiency of curved and flat wing.
(_a_) Air flow past curved wing is smooth without much eddying; (_b_)
air flow past flat wing produces eddies above it.]
The question of wing curvature is exceedingly important then; we find
that the curvature of its upper surface is particularly so. We notice
that airplane wings all have a certain thickness in order to enclose
the spars and ribs; it is not necessarily a disadvantage for them to
be thick, due to the fact that the upper curve of the wing does most
of the lifting anyway, and the lower side is relatively unimportant.
You can make the lower surface almost flat, without much hurting the
effect of the wing, so long as the upper surface remains properly
curved. However, the upper surface must be accurately shaped, and is
so important that in some machines we find cloth is not relied on to
maintain this delicate shape, but thin wood veneer is used (I refer to
the front upper part of the wing). In general, then, wings are thick
toward the front and taper down to a thin trailing edge.
[Illustration: FIG. 22.—Diagram of vacuum and pressure on airplane
wings.
Note in biplane reduced vacuum on bottom wing.]
You may wonder how it was found that the upper surface of the wing was
the most important; and I will say that this was one of the interesting
discoveries of the early history of aerodynamics. People at first
thought that a wing sweeping through the air derived its support
entirely from the air which struck the bottom of the wing, and they
assumed that if the bottom of the wing were properly shaped, the top
did not matter; that is, all the pressure in the air was delivered
up against the bottom surface. But a French experimenter conceived
the idea of inserting little pressure gages at various points around
the wing. He found, it is true, that there was considerable pressure
exerted in the air against the bottom of the wing; but he found a more
surprising fact when he measured the condition above the wing. When he
applied his gage to the upper surface of the wing, it read backward,
that is, showed a vacuum, and a very pronounced one. He found that
there was a vacuum sucking the top part of the wing upward twice as
hard as the pressure underneath was pushing; so that two-thirds of the
total lift on this wing was due to vacuum above it (see Fig. 22).
In the diagram the shaded area on top of the wing represents vacuum
above, that below the wing represents pressure beneath.
[Illustration: FIG. 23.—Wings of small and large aspect ratio]
=Aspect Ratio.=—The third factor in wing efficiency has to do with
the plan shape. It was early found that square wings were not much
good, and that if you made them wide in span like those of a bird, the
efficiency was best (see Fig. 23). Aspect ratio is the term which gives
the relation of the span to the fore and aft dimension of the wing,
and this relation is usually equal to six or so. The reason why large
aspect ratios are advantageous is as follows:
The tips of all wings are inefficient, because they allow the air
to slip sideways around the ends, and there is all the trouble of
disturbing this air without extracting any considerable lift from
it. In a wide-span wing these inefficient wing tips are only a small
percentage of the total area, but in a small-span wing they may be an
important consideration (see Fig. 24).
[Illustration: FIG. 24.—Diagram illustrating aspect-ratio effect.
Arrows show direction of air flow past plate; note that air escapes
sideways around sides of plate. This phenomenon occurs at the tips of
all airplane wings and accounts for small efficiency of narrow-span
wings. ]
=Wing Arrangements.=—All the foregoing remarks in this chapter have
applied only to a single wing. They apply in general to double or
triple wings (biplanes and triplanes), but the matter of arranging
multiple wings affects the efficiency.
The monoplane with its single layer of wings is the most efficient type
of flying machine. We find if we arrange wings into the biplane shape
that the presence of the upper wing interferes with the vacuum formed
above the lower wing, and the efficiency decreases (see Fig. 22). The
same is true of the triplane and the quadruplane arrangement. If all we
wanted in airplanes was efficiency, we would use monoplanes, but the
biplane is pretty popular now in spite of its low efficiency; this is
because it can be much more strongly trussed than the monoplane, and
also because of the fact that sufficient area may be secured with less
span of wings.
It may be said that the low efficiency of the biplane can be somewhat
relieved by spacing the upper and lower wings at a considerable
distance apart; but if they are spaced at a distance much greater than
the chord, it requires extra long struts and wires, and the resistance
and weight of these will offset the advantage of wider spacing; so that
practically biplane-wing efficiency may be taken as 85 per cent. of
monoplane efficiency.
It remains to mention the tandem arrangement, used in all airplanes,
where the tail is a tandem surface in conjunction with the wings.
A surface located in the position of an airplane tail is at a
disadvantage and shows low efficiency for flight purposes. This is
because the main wings deflect the air downward and when the tail comes
along it meets air which has a more or less downward trend, instead of
encountering fresh, undisturbed air (see Fig. 16).
=Resistance of an Airplane to Motion.=—Earlier in this chapter the
support of an airplane was explained and it was seen that the weight
was exactly equalled by the lift or support; it was also explained that
the production of this lift required considerable force in moving the
wings rapidly through the air. It is not only the wings, however, which
require force to overcome the resistance to motion. In order to have
any wings at all it is unfortunately necessary to supply also struts,
wires, etc., for bracing these wings, also a motor and seat for the
passenger, which are usually included inside a fuselage, also wheels
for landing and various control surfaces. None of these accessories to
the wings contribute material lift, but they involve a large amount of
resistance which is therefore a dead loss. Note carefully that there
are two distinct sorts of resistance: (1) that of the wings, which is
the necessary price paid for securing lift; (2) that of all the rest
of the machine, in return for which nothing beneficial is received,
and which therefore has sometimes been called “parasite” or “deadhead”
resistance.
In a typical training machine the total resistance to be overcome if
forward motion is maintained is as follows: (See Fig. 26.)
_At 72 miles per hour_:
Wings 160 lb.
Deadhead {Fuselage 75}
resistance {Wiring 70}
{Struts 20} 195
{Miscellaneous}
{ Balance 30}
———
Total 355 lb.
_At a speed of 57 miles per hour_:
Wings 158 lb.
Deadhead resistance 130
———
Total 288 lb.
_At a speed of 43 miles per hour_:
Wings 350 lb.
Deadhead resistance 125
———
Total 475 lb.
It is seen that the above resistance values total to the highest figure
at the lowest speed, and that the lowest value of resistance occurs at
an intermediate speed; the resistance decreases as the speed decreases
from 73 to 57 miles per hour; but a further decrease in speed finds the
resistance running up rapidly so that at minimum speed the resistance
is very great again. This is due to the fact that at high speeds the
deadhead resistance exceeds that of the wings but at slow speeds
although the deadhead resistance is very small, the wings being turned
up to a large angle within the air, have a resistance which is at its
maximum. This seems clear enough when we remember that the lift of the
wings remains the same as the angle decreases (and speed goes up) but
that the efficiency of the wings increases so that the wing resistance
is a smaller fraction of the lift at high speed than at low speed.
=Cause of Resistance.=—Wing resistance, which is affected, as mentioned
previously, by the wing curvature, can not be decreased unless new and
improved sorts of wings are invented. As to deadhead resistance, it
may be decreased in future by methods of construction which eliminate
unessential parts. In a high-speed airplane in this country an attempt
was made to eliminate the wires altogether and most of the struts
(because the wiring is one of the largest single items of deadhead
resistance); so far the attempt has failed for structural reasons. In
the monoplane type of airplane of course the struts are eliminated,
which is an advantage from the standpoint of resistance.
[Illustration: FIG. 25.—Diagram illustrating advantage of stream-line
shape.
Note large eddy disturbance and vacuum behind round shape, causing high
resistance.]
As long as struts, wires, etc., are used at all, the minimum resistance
can be secured by giving them a proper “stream-line” shape. The
stream-line shape is one in which the thickest part is in front and
tapers off to a point in the rear, like a fish. If, for instance, we
take round rods instead of the struts of the training machine above
mentioned and having the same thickness, the resistance might be 80
lb. instead of 20 lb.; and if we take a rod whose shape is elliptical
with its axes in a ratio of 1 to 5 the resistance might be 40 lb.
instead of 20 lb.; and if we took the stream-line struts out of the
training machine and put them back sharp edge foremost, the resistance
would be increased. The advantage of the stream-line shape is that it
provides smooth lines of flow for the air which has been thrust aside
at the front to flow back again without eddies to the rear. This is not
possible in the case of the round strut, behind which will be found a
whirl of eddies resulting in a vacuum that tends to suck it backward.
By fastening a stream-line tail behind the round rod the eddies are
greatly reduced, as is the vacuum. The wires of the airplane are
subject to the same law and if the training machine above mentioned had
stream-line wires instead of round wires we might expect them to have
less than 70 lb. resistance. The fuselage should always be given as
nearly a stream-line shape as the presence of the motor and tanks will
permit; and it must all be inclosed smoothly in “doped” fabric in order
that the air-flow phenomena may operate. As for the wheels, they must
of necessity be round, but by enclosing them with fabric the air flow
past them is more easy and the resistance may be halved.
=Total Resistance.=—The necessity has been explained of discriminating
between wing and deadhead resistance; if we are talking about wings
we may ignore everything except the wing resistance (commonly called
“wing drift”), but if we are talking about the whole airplane, we then
must refer to the total resistance, which includes all the others and
is overcome by the propeller thrust. “Skin-friction” resistance has not
been mentioned nor need it be more than to say that any surface moving
through air attributes part of its resistance to the actual friction of
the air against it, and therefore should be as smooth as possible.
=Motor Power Required for Flying.=—The reason resistance interests us
is that motor power is required to propel the airplane against it; more
and more power as the resistance and speed increase. Obviously, the
power required is least when the resistance is small, _i.e._, when the
speed is intermediate between minimum and maximum. It takes more power
to fly at minimum speed than at this intermediate speed. Of course
it also takes more power to fly at maximum speed, where again the
resistance is high.
=Maximum Speed.=—Ordinarily, for moderate speeds, airplanes have a
margin of power at which the throttle need not be opened wide; should
speed be increased the resistance and horsepower required will increase
steadily until the throttle is wide open and motor “full out;” this
establishes the maximum speed of an airplane; there is no margin of
power, no climb is possible. The only way to increase speed is to
use the force of gravity in addition to the motor force. It may be
interesting to know what is the maximum possible speed in the case
of a vertical dive with the motor shut off; it will be about double
the maximum horizontal speed as may be readily seen from the fact that
the thrust in the direction of motion is now no longer horizontal and
equal to the resistance but is vertical and equal to the weight of the
machine; that is, the thrust may be increased fivefold, and the speed
resulting will be increased correspondingly, if the motor be running in
such a vertical dive the velocity may be slightly increased though at
this speed of motion the propeller would not have much efficiency.
There is danger in such high speeds; the stresses in the machine are
increased several times merely by the increased resistance, and if the
angle of incidence should be suddenly brought up to a large value at
this high speed the stress would again be increased so that the total
stress increase theoretically might be as high as fourteen times the
normal value, thus exceeding the factor of safety. It is for such
reasons that the maximum strength is desirable in airplanes; holes
must not be carelessly drilled in the beams but should be located if
anywhere midway between the top and bottom edges, where the stress will
be least; initial stresses, due to tightness of the wires, should not
be too great.
=Climbing Ability.=—Climbing ability refers to the number of feet of
rise per minute or per 10 min. In order to climb, extra horsepower
is required beyond that necessary for more horizontal flight. The
machine can, for instance, fly at 56 miles per hour at which speed
it requires 43 hp. If now the throttle is opened up so as to increase
the horsepower by 22, making a total of 65 hp., the machine will climb
at the rate of 380 ft. per minute, maintaining approximately the same
flight speed. If instead of 65 hp., it were 54 hp. the speed of climb
would be about one-half of the 380, or 190 ft. per minute; the flight
speed again remaining approximately as before; that is, any margin
of horsepower beyond the particular value of horsepower required may
be used for climbing without material change of the flight speed. It
is necessary here to state that lift does not increase during climb;
and while for the instant that a climb commences there may be, due
to acceleration, more lift on the wings than balances the weight,
this does not remain true after a steady rate of climb is reached.
To illustrate, in a wagon drawn uphill by horses the wheels which
support the wagon do not exert any more support than on the level, and
the entire force to make the wagon ascend is supplied through extra
hard pulling by the horses. Thus in a climbing airplane the propeller
furnishes all the climbing force and lift is no greater than in
horizontal flight. In fact, the actual lift force may be even less, as
the weight of the airplane is partly supported by the propeller thrust
which is now inclined upward slightly.
To secure maximum climbing ability, we must determine at what velocity
the margin of motor power is the greatest. In the above-mentioned
machine we know that the horsepower required for support is least for
a speed of near 55 miles per hour, and it is near speed where therefore
the excess margin of power is greatest and at which climbing is best
done. An airplane designed chiefly for climbing must have low values of
motor power necessary for support, namely, must have small resistance,
therefore small size, therefore small weight.
[Illustration: FIG. 26.—Performance curves for typical training
airplane.]
=Gliding Angle.=—Gliding angle denotes the angle at which the airplane
will glide downward with the motor shut off and is spoken of as 1 in 5,
1 in 6, etc., according as it brings the airplane 1 mile down for each
5, 6, etc., miles of travel in the line of flight. The gliding angle of
a machine may be found by dividing the total resistance into the weight:
Gliding angle = Weight/Total resistance.
In the above-mentioned airplane it is one in 6.6 when the resistance
is 288 lb., that is, when the speed is 57 miles per hour. At any other
speed the resistance increases and hence the gliding angle decreases.
Hence the importance of putting the airplane into its proper speed in
order to secure the best gliding angle.
=The Propeller.=—The propeller or “screw,” by screwing its way forward
through the air, is able to propel the airplane at the desired
velocity. Regarding principles of propeller action the matter can be
hastily summarized in the following brief lines. The propeller blades
may be regarded as little wings moving in a circular path about the
shaft; and they have a lift and drift as do the regular wings. The lift
is analogous to the thrust; to secure this thrust with least torque
(drift) the blades are set at their most efficient angle of incidence,
and while the blade appears to have a steep angle near the hub, it
actually meets the air in flight at the same angle of incidence from
hub to tip.
=Propeller Pitch.=—Pitch is best defined by analogy to an ordinary
wood-screw; if the screw is turned one revolution it advances into
the wood by an amount equal to its pitch. If the air were solid, a
propeller would do the same, and the distance might be 8 ft., say.
Actually the air yields, and slips backward, and the propeller advances
only 6 ft. Its “slip” is then 8 minus 6, equals 2 ft., or 25 per cent.
Such a propeller has an 8-ft. pitch, and a 25 per cent. slip.
This “slip stream” blows backward in a flight so that the tail of an
airplane has air slipping past it faster than do the wings. Hence the
air forces at the tail are greater than might be expected. The rudder
and elevators therefore give a quicker action when the propeller is
rotating than when, as in the case of a glide, it is not.
[Illustration: FIG. 27.—Washout in left-wing tips.]
=Washout.=—Due to torque of the motor, the airplane tends to rotate
in the opposite direction to the propeller. This tendency may be
neutralized by giving one wing tip a smaller angle of incidence,
called “washout,” so that the machine normally tends to neutralize the
torque-effect.
PRINCIPLES OF AIRPLANE EQUILIBRIUM
[Illustration: FIG. 28.—Balances of forces in an airplane.
Weight forward of lift, thrust below resistance. Thrust equals
resistance, weight equals lift.]
=Introductory.=—Under this head will be discussed: (_a_) features of
airplane design which tend to maintain equilibrium irrespective of the
pilot; (_b_) matters of voluntary controlling operations by the pilot.
As regards (_a_) the tendency of the airplane toward inherent stability
acts to oppose any deviation from its course whether the pilot so
desires or not. The more stable is a machine, the less delicately is it
controlled, and the present consensus of opinion among pilots is that
a 50-50 compromise between stability and controllability is the best
thing.
In questions of airplane equilibrium the starting point is the center
of gravity; obviously, if the center of gravity were back at the tail
or up at the nose there would be no balance; the proper place for
it is the same spot where all the other forces such as thrust, lift
and resistance act; there it is easy to balance them all up. But it
is not always easy to bring the line of thrust and the line of total
resistance into coincidence, because the line of thrust is the line
of the propeller shaft and when this is high up as in the case of
some pushers it may be several inches above the line of resistance.
And as the thrust is above the resistance there is a tendency to nose
the machine down; to balance which the designer deliberately locates
the center of gravity sufficiently far behind the center of lift so
that there is an equal tendency to tip the nose upward; and all four
forces mentioned completely balance each other. But things may happen
to change the amount or position of these forces during flight, and if
this does happen the first thing to do is to restore the balance by
bringing in a small new force somewhere. In an actual airplane this
small restoring force is supplied at each critical moment first, by
the tail, etc., of the airplane and second, by voluntary actions of
the pilot. The center of gravity of any airplane may be determined
easily by putting a roller under it and seeing where it will balance,
or by getting the amount of weight supported at the wheels and tail,
according to the method of moments.
=Longitudinal Stability.=—Longitudinal stability has to do with the
tendency of an airplane to maintain its proper pitching angle. It was
said above that the four forces of lift, resistance, thrust and weight
always exactly balanced due to their size and their position. Now the
first consideration about longitudinal stability is that while the
centers of gravity and other forces remain in a fixed position, the
center of lift changes its position whenever the angle of incidence
(that is the speed) is changed. The phenomenon of shift of center of
pressure applies only to the wings and to the lift (the position of
center of resistance remains practically fixed at all angles).
Note the effect on center of pressure position of a change of wing
angle (see Fig. 20). The wing used on the U. S. training machine has a
center of lift which is about in the middle of the wing when flying at
a small angle of maximum speed; but if the angle is increased to the
stalling angle of 15°, the center of pressure moves from midway of the
wing to a point which is about one-third the chord distance of the wing
from the front edge. The lift may travel about ½ foot, and it is equal
in amount to the weight of the machine (that is, nearly a ton), and
the mere effect of changing the angle from its minimum to its maximum
value therefore tends to disturb the longitudinal equilibrium with a
force which may be represented as 1 ton acting on a lever arm of ½ ft.
Suppose that the airplane is balancing at an angle of 2° so that the
center of gravity coincides with the center of lift for this angle; now
if a gust of wind causes the angle to increase for an instant to 2¼°,
the center of lift will move forward and tend to push the front edge of
the wing up, thus increasing the angle further to 2½°. Then the center
of lift, of course, moves further forward to accommodate the increase
of angle, and in a fraction of a second the wing would rear up unless
it were firmly attached to the airplane body and held in its proper
position by the tail. Similarly if for any reason the proper angle of
2° were decreased, the same upset would follow, only this time tending
to dive the wing violently to earth. This tendency is neutralized in an
airplane by the “Penaud Tail Principle.”
There are certain shapes of wings in which the center of pressure
travels in the reverse direction; a flat plate, for example; or a wing
having its rear edge turned up so that the general wing shape is like
a thin letter “S.” Such wings as these would not tend to lose their
proper angle, because when the angle is changed for any reason the
center or pressure in these wings moves in just the manner necessary to
restore them to their proper position; but these wings are inefficient
and are not in present use on airplanes.
[Illustration: FIG. 29.—Diagrams illustrating theory and application
of longitudinal dihedral angle.]
=The Penaud Tail Principle.=—_Rule._—The horizontal tail must have a
smaller angle of incidence than the wings. The upsetting force above
mentioned must be met by a strong opposite righting force, and this
latter is furnished by the horizontal tail surface. In the angle of
equilibrium of 2° above mentioned, the flat horizontal stabilizer will
perhaps have no force acting on it at all because it is edgewise to
the air and its angle of incidence is zero. When the angle of the wing
increases to 2¼° and the lift moves forward tending to rear it up,
the wing being rigidly fastened to the body pushes the tail downward
so that the tail now begins to have a small lift force upon it due to
its angle of ¼°; and this newly created force, though small, acts at
such a long lever arm that it exceeds the rearing force of the wing
and will quickly restore the airplane to 2°. This action depends upon
the principle of the Penaud Tail or longitudinal “Dihedral” which
requires that the front wings of an airplane make a larger angle with
the wind than the rear surface. This principle holds good even when
we have rear surfaces which actually are lifting surfaces in normal
flight, the requisite being that the wings themselves shall in such
cases be at an even greater angle than the tail. No mention has been
made of the elevator control, because its action is additional to the
above-mentioned stability. The elevator is able to alter the lift on
the tail; such alteration requires, of course, immediate change of
angle of the wings so that equilibrium shall again follow; and this
equilibrium will be maintained until the lift at the tail is again
altered by some movement of the elevator control. Thus the elevator may
be considered as a device for adjusting the angle of incidence of the
wings.
The air through which the wings have passed receives downward motion,
and therefore a tail which is poised at zero angle with the line of
flight may actually receive air at an angle of -2° or -3°. In the above
case we would expect an actual downward force on the tail, unless this
tail is given a slight arch on its top surface (for it is known that
arched surfaces have an angle of zero lift which is negative angle).
=Longitudinal Control.=—Steering up or down is done by the elevator,
which as explained above is merely a device for adjusting the angle
of incidence of the wings. The elevator controls like all the other
controls of an airplane depend for their quick efficient action upon
generous speed; they can not be expected to give good response when the
machine is near its stalling speed. The elevators like the rudder are
located directly in the blast of the propeller and in case the speed
of motion should become very slow, the elevators may be made to exert
considerable controlling force if the motor is opened up to blow a
strong blast against them. This is good to bear in mind when taxying
on the ground because if the motor is shut off at the slow speed of
motion the elevator and rudder will lose their efficacy. The propeller
blast, due to a 25 per cent. slip, adds 25 per cent. of apparent speed
to those parts which are in its way, and therefore the tail forces are
affected as the square of this increase, that is, the forces may be 50
per cent. greater with the propeller on than off.
=Lateral Stability.=—This depends upon the keel surface or total side
area of an airplane. The keel surface includes all the struts, wires,
wheels, wings, as well as body, against which a side wind can blow.
Skidding and side-slipping have the same effect as a side wind, and
the resulting forces acting against the side of the machine should be
made useful instead of harmful. This is done by properly proportioning
the keel or side surface. If keel surface is low, the side force will
rotate the airplane about its axis so that the windward wing sinks; if
high, so that it rises. But if the keel surface is at just the right
height (_i.e._, level with the center of gravity) the side forces will
not rotate the machine at all and will simply oppose the skidding
without upsetting equilibrium.
[Illustration: FIG. 30.—Diagram showing effect on lateral stability of
dihedral angle and non-skid fins.
(_a_) Machine flying level. (_b_) Machine tips and side-slips: excess
pressure is created on windward wing and fins, (_c_) Machine has
side-slipped and rotated back to level. ]
=Lateral Dihedral.=—Now when an airplane appears to have its
keel-surface center too low, the easiest way to raise it level with the
center of gravity is to give the wings a dihedral angle, that is make
them point upward and outward from the body. Thus their projection, as
seen in a side view, is increased, and the effect is to add some keel
surface above the center of gravity, thus raising the center of total
keel surface.
A further advantage of the lateral dihedral is that any list of the
airplane sideways is automatically corrected (see Fig. 30). The low
wing supports better than the high wing, because a side slip sets in,
hence will restore the airplane to level position.
=Non-Skid-Fins.=—Where for the above-mentioned purposes an excessive
dihedral would be needed, resort may be had to non-skid-fins erected
vertically edgewise to the line of flight above or beneath the topwing.
These are used in marine machines to balance the abnormally large keel
surface of the boat or pontoon below.
=Lateral Control.=—By means of ailerons, lateral control is maintained
voluntarily by the pilot; the aileron on the low tip is given a greater
angle of incidence while on the high tip a less angle of incidence
thus restoring the proper level of the machine. Notice that the
efficacy of the ailerons depends upon speed of motion of the airplane,
irrespective of propeller slip because the propeller slip does not
reach the ailerons. Therefore, at stalling speeds the ailerons may not
be expected to work at their best, and when lateral balance is upset at
slow speeds it is necessary to dive the machine before enough lateral
control can be secured to restore the balance.
[Illustration: FIG. 31.—Deperdussin control.
System used in U. S. training airplanes.]
=Directional Stability.=—Directional stability has to do with the
tendency of an airplane to swerve to the right or left of its proper
course. To maintain directional stability the “vertical stabilizer” is
used, which acts in a manner analogous to the feather on an arrow. Thus
in case of a side slip the tail will swing and force the airplane nose
around into the direction of the side slip so that the airplane tends
to meet the relative side wind “nose-on” as it should. The vertical
stabilizer should not be too large, however, as then any side pressure
due to deviation from a rectilinear course will cause the machine to
swerve violently; the wing which is outermost in the turn will have
preponderance of lift due to its higher speed; that is, the airplane
will get into a turn where there is too much bank and a spiral dive may
result.
=Directional Control.=—The rudder gives directional control in
exactly the same way that it does on a boat; it should be said,
however, that the rudder is sometimes used without any intention
of changing the direction, that is, it is used simultaneously with
the ailerons as a means of neutralizing their swerving tendency.
The ailerons, of course, at the same time that they restore lateral
balance create a disadvantageous tendency to swerve the machine away
from its directional course; that is what the rudder must neutralize.
Moreover, the rudder is frequently used against side winds to maintain
rectilinear motion.
=Banking.=—Banking combines the lateral and directional control, which
should be operated simultaneously so as to tilt the machine and at the
same time maintain the radius of turn. The wings are tilted in a bank
because in going around a curve of a certain radius the weight of the
machine creates a centrifugal force in a horizontal direction and if
the curved path is to be maintained this centrifugal force must be
neutralized; and this is done by inclining the force of lift inward
until it has a horizontal component equal to the centrifugal force.
That is why the angle of bank must be rigidly observed, or else the
inward component of the lift will change. Now as soon as the wings bank
up, the lift force is no longer all vertical and therefore may not be
enough to support the weight of the machine. To offset this have plenty
of motor power for speed in a bank; and do not try to climb while
banking.
It is better to bank too little than too much; too little results in
skidding which may be easily cured; too much results in side slipping
inward and if the tail surface is too great in this latter case, a
spiral dive may result—so look out for over banking.
It is better for the beginner in banking to move his ailerons first and
then move the rudder; for if he moves the rudder first there will be
skidding outward, forward speed will drop and a stall may result. On
high angles of banking, over 45°, it should be noted that the elevators
are now more nearly vertical than horizontal and operate as a rudder;
similarly the rudder’s function is reversed, and to turn down the
rudder will be used.
=Damping in an Airplane.=—Above have been mentioned the restoring
forces which tend toward airplane equilibrium. Now these restoring
forces tend to push the machine back to equilibrium and even beyond
in exactly the same way that gravity causes a pendulum to swing about
its point of equilibrium. This can sometimes be noticed in the case
of an automobile when travelling at high speed along country roads
where a sort of slow oscillation from side to side may be noticed due
to the forceful maintenance of equilibrium of the body in its forward
motion. This oscillation in an airplane would be serious unless there
were means of damping it out and these means are: first, the wings;
second, the tail surfaces; third, the weight and inertia of the machine
itself. Regarding inertia it should be said that a machine with weight
distributed far from the center of gravity, such as the double-motor
airplane has a large tendency to resist the rolling motions associated
with lateral stability. But from the same sign airplanes with large
moment of inertia are difficult to deviate from any given attitude, and
therefore have the name of being “logy.” The proper proportioning of
an airplane’s parts to secure first, the restoring forces; second, the
proper damping force; third, the proper amount of moment of inertia, is
a very delicate matter and beyond the scope of the present chapter.
CHAPTER IV
FLYING THE AIRPLANE
=Starting Off.=—The first thing to do before starting off in an
airplane is to inspect carefully everything about the machine and
assure yourself that it is in perfect condition.
When all is ready to start turn the machine directly against the wind;
this is done in order that the rise from the ground may be more quickly
made with the assistance of the wind under the wings, and it has a more
important advantage in the fact that if you try to get off the ground
across the wind the machine will be very hard to balance. Birds also
take the air directly against the wind even though for the moment this
carries them in a direction toward some supposed enemy, and it is a
fundamental principle in airdromes. Keep the machine pointed into the
wind for the first 200 ft. of altitude (and similarly in landing face
the wind when within 200 feet of the ground). In case the engine should
fail before a height of 200 ft. is reached, never turn down wind as
this is extremely dangerous.
Assistance will be had for the start from the mechanics, or if away
from the airdrome from bystanders. Have each assistant in his proper
place before starting the engine; one is to start the propeller and the
rest to hold back the machine until ready to let go.
[Illustration:
(_From “How to Instruct in Flying.”_)
FIG. 32.—Airplane in flying position just after starting.
This cut also illustrates proper landing attitude, since airplane is
just skimming the ground.]
In order to get off the ground you will want good engine power; it
takes considerable thrust to accelerate an airplane on the ground to
its flying speed; in fact the first flying machine of the Wrights had
to use an auxiliary catapult to furnish the thrust necessary to get
them into the air. Making sure that the motor is giving full power
raise the hand as a signal to the attendants to remove the chocks and
let go. As you start rolling forward push the control lever forward
which will raise the tail off the ground and place the wings edgewise
to the wind while they will not offer resistance to the acquiring of
good rolling speed. Within a few seconds the machine will have attained
on the ground a velocity not less than the low flying speed; it will
not rise, however, until the tail is lowered by pulling the lever
back. When the necessary rolling speed is attained pull the lever
softly backward; the tail at once drops, the wings increase their angle
and lift and the machine will rise, the lever being held in a fixed
position (see Fig. 32). The distance between the point of starting
and rising will be 100 yd. or more and will occupy from 5 to 10 sec.
depending on the wind.
The change from flying position to climbing position is only a slight
modification involving only a slight pulling back of the control lever
and holding it in fixed position; the motor may in some machines simply
be opened out when its increased power will make the machine rise;
however, there is only one speed at which the climb will be fastest and
therefore it is well to know what is the proper speed for climbing; the
motor is then opened out full and the airplane operated to give the
proper speed corresponding.
The pupil should rise to the height of at least 100 ft., as any less
is useless and nothing will be learned from landing. In the case of
cross-country flying the pilot will rise to the height of 2000 ft.,
circling over the field rather than flying off in a straight line so
that preparatory to his start he always has the flying field in reach.
[Illustration:
(_From “How to Instruct in Flying.”_)
FIG. 33.—Airplane in gliding position, approaching a landing.
Note that its attitude relative to line of flight is similar to “flying
position,” line of flight however being inclined.]
=Landing.=—Proper landing is the most important thing in airplane
flying. The pilot in turning his machine downward toward a landing
spot from flight will choose a distance from the field equivalent to
the proper gliding angle of his machine. If the gliding angle is 1 in
7 he must not turn downward any further from the field than a distance
greater than seven times his altitude or he will fall short. It is
safer to come closer to the field before turning downward for two
reasons: first, because you may not be gliding at the best gliding
angle; second, because you can always kill extra height by a spiral or
two better than you can regain it. Have height to spare when landing.
To come down throttle down the engine and push the lever softly forward
until the proper gliding angle is obtained (Fig. 33). The reason for
throttling down the engine is: first, that you do not need its thrust
when you are coasting down because gravity furnishes all the necessary
velocity; second, if you glide or dive with the motor wide open high
speed will result, resulting in strains on the machine especially
on the moment of leveling out again; third, at this high speed the
controls become stiff to operate.
[Illustration: FIG. 34.—Attitudes of an airplane in flight.]
Maintain the proper gliding speed to within 5 miles an hour of what
it ought to be as it is the speed which determines the proper gliding
angle. The revolution counter will indicate what the speed is or the
air-speed meter may be used. Arrange to come on to the field facing
directly into the wind, which may be observed by watching smoke or
flags below. In landing against the wind you are again copying the
practice of the birds. When you come to within 15 ft. of the ground
pull the lever softly back until the machine is in its slow-flying
position, which should be attained 5 ft. above the ground (Fig. 34).
Hold the stick at this position of horizontal flying; no further
movement of the lever is necessary except to correct bumps, for which
purpose it would be held lightly for instant action. The aileron
control must be used here to keep the machine level and it may be
necessary to operate the rudder after touching the ground in order to
avoid swerving; in fact some machines are provided with a rear skid
which steers for this purpose.
In rolling just after landing keep the tail as close to the ground as
possible without causing undue bumping, so that the maximum resistance
of the wings may be presented to the air and the machine be slowed up
rapidly. Some machines are fitted with brakes on the wheels to assist
in the quick retardation of the roll. Landing is one of the biggest
problems in aviation and is a hard thing to learn because it is done
at a high speed especially in the fast military machines such as the
Fokker, Nieuport, etc. Landing is more of a problem than it used to be
in the early days when, for instance, the Wrights were able to land
without any wheels at all on mere skids because their machines were not
fast.
The following are examples of bad landings:
1. The pancake results from allowing the machine to get into its rising
position when it is landing (Fig. 35). There will be a perpendicular
bounce and on the second bounce the running gear will break. In order
to get out of an imminent pancake open up the engine to keep machine
flying, put the machine into a flying position, then throttle down
again and land.
2. Another type of pancake results from bringing the machine out of
its gliding position at a point too far above the ground when the
machine will drop due to lack of speed and break the running gear. To
avoid this open motor full, thus regaining speed and flying position;
afterward throttle down and reland.
[Illustration:
(_From “How to Instruct in Flying.”_)
FIG. 35.—Bad landing, Type 1—the “pancake” landing.
Line of flight is downward; angle of incidence large, hence speed is
slow; but there is too much downward momentum and landing gear will
break. Should line of flight arrow point upward, airplane as shown
would then be in climbing position. ]
3. A third type of bad landing results from failure to turn the machine
out of its glide at all, so that it glides straight downward until
it touches the ground. This is the most dangerous case of all the
bad landings. To cure it open up the engine after the first bounce,
regaining flying speed before the second bounce; then reland.
[Illustration:
(_From “How to Instruct in Flying.”_)
FIG. 36.—Bad landing Type 4—machine not level.
Wheels do not touch ground at same time, and one may smash.]
4. If at the moment of landing the rudder is turned causing machine to
swerve, or if the machine is not level, a side strain will be placed
upon the landing gear and the wheels will buckle (Fig. 36).
CHAPTER V
CROSS-COUNTRY FLYING
Cross-country flying differs from ordinary airdrome flying in that
it takes you a long way off from your landing field. On the airdrome
your chief anxiety is to learn how to fly, how to work the controls,
how to bank; but in cross-country work, you are supposed to have all
the technique of airplane operation well in hand, so that you do not
have to think much about it. In cross-country flying, then, your chief
anxiety will be to arrive at your destination and to be constantly
searching out available landing fields in case of engine failure. The
first cross-country flight you make may be a short, easy one, in which
there are plenty of available landing places, and on which you will be
able to make a regular reconnaissance report. Further experience in
cross-country work will involve more and more difficult trips, until
you will think nothing of flying, for example, on long raiding tours
over unfamiliar enemy country.
=Equipment.=—Knowing that you may have to land far away from any
headquarters, you must take a complete set of tools and covers for the
airplane. Your clothing need not be different from usual, and will
comprise helmet, goggles, leather suit, and gloves. Do not forget your
handkerchief, which you frequently need to clean off your goggles.
The instruments needed on a cross-country trip are: a compass, which
should be properly adjusted before starting and the variation angle
noted. A wrist watch is necessary; ordinary dashboard clocks go wrong
on account of the vibration. Take an aneroid barometer with adjustable
height reading. Of course you will depend upon a revolution indicator,
for no matter how experienced a pilot may be in “listening out” faulty
engine operation, after a long flight his ear loses its acuteness,
and he will fall back on the revolution indicator for assistance. The
air-speed meter, whether of the Pitot type or pressure-plate type, will
prove invaluable in flying through clouds or mist when the ground is
obscured. Also the inclinometer is able to give the angle of flight
when the earth is not visible, although the speed indicator usually is
sufficient to give the angle of flight, for an increase of speed means
downward motion and decrease of speed means upward motion. Additional
instruments may be used.
=Map.=—The map is essential for cross-country work. It should be tacked
on to the map board if the flight is short, but made to run on rollers
if the flight is long. In the latter case the map is in the form of a
single long strip, while your flight may be full of angles; therefore
you will have to practice using this sort of map, in which the corners
of your flight are all drawn as straight lines. The scale of maps may
be 2 or 4 miles to the inch for long flights. This scale is sometimes
spoken of as a fractional figure; that is, 2 miles to the inch is the
same as 1/127,000 scale. The map should be studied most carefully
before the start of the trip. The course which you propose to fly
should be marked out on it; all available landmarks which could be of
service as guides should be distinctly noticed and marked on the map
where necessary. These landmarks will in case there is no wind enable
you to make your trip without using the compass at all, and in case of
wind, are essential as a check on the compass. Mark off the distance
in miles between consecutive points of your course. Mark the compass
bearing of each leg of this course.
As landmarks towns are the best guides, and they should be underscored
on the map, or enclosed in circles. It is customary not to fly actually
over towns. Railways are very good assistance to finding your way,
and these should be marked on the map in black wherever they approach
within 10 miles of the course. Mark water courses with blue color, and
roads with red.
=Landmarks.=—Only practice can make a pilot good at observing the
various features of the ground beneath him. The various features which
can be used as guides are those which are most visible. After towns,
railways come next in importance. Their bridges, tunnels, etc., make
good landmarks. On windy days when relying on the compass, it will be
well to keep in sight of a railway even if this be the longer way
around, because the railway gives a constant check upon the compass
bearing. In this case you will have noted on your map a general
magnetic bearing of the railway, which bearing you can readily compare
with your compass reading. Moreover, the railway is good in case you
become involved in a fog or mist for a time. It should be remembered,
however, that on most of the maps no distinction is made between one
and two-track roads; also that it is easy to make mistakes where branch
lines are not shown on the map because they are dead ends leading
to private quarries, etc., and may be taken for junctions. Railways
sometimes seem to end abruptly, which means that you are looking at a
tunnel.
Water is visible from a great distance. Cautions to be observed
are that after a heavy rain small flooded streams may take on the
appearance of larger bodies of water or lakes, which you will have
difficulty in reconciling with the map. Small rivers are often overhung
with foliage, and to follow them in all their curves will waste a lot
of time.
The use of roads as guides may be governed by the fact that paved roads
are usually main roads, and telegraph wires may be expected along
them. In the newer parts of the United States the system of laying out
roads provides a very useful means of gaging distances; I refer to
the section system which is in use, for instance, in Illinois, where
there is a road every mile running north and south, so that the entire
country is cut up into squares 1 mile on each side, with occasional
roads of course at ½-mile and ¼-mile points.
=Navigation by Landmarks.=—In all cases of cross-country flying the
pilot will have two independent systems of maintaining his proper
directions: first, the computed compass bearing; second, the use of
landmarks whose position is known. In comparing his computed course
with the course actually indicated by passing over these landmarks
the rule should be made that, in case of doubt when a landmark is
not distinctly recognized, take the compass course; there are many
chances that a landmark may be altered or even removed without being
so recorded on the pilot’s map, whereas the errors of the compass of
course are presumably understood by the pilot who has secured every
opportunity to check it when passing previous landmarks.
It is important to note the time of completing successive stages of the
flight, that is when passing over predetermined landmarks. Time is a
very uncertain condition to ascertain in airplane flying for it seems
to pass quickly on calm days but slowly when the journey is rough. If
the pilot does not check the time interval between successive objects
he is quite likely to expect the next before it is really due.
=Landing Fields.=—Next to the ever-present worry which the pilot has
regarding the perfect operation of his engine, the most important
thing about cross-country flying is that wherever he may be he must
have available a landing field within gliding distance in case his
engine defaults. The question is of course immediately raised, “What
if there is no landing field within gliding range?” The answer to this
is that the pilot will instinctively learn to keep his eyes open for
landing possibilities every minute of his progress whether he expects
to use them or not; in cross-country flying the lookout for fields is
first and foremost in his mind; if there are no fields, it is up to
him to pick out a spot of ground which is the least objectionable for
a landing. In the State of Illinois the question of landing fields
is almost non-existent, because there are large, flat fields and
pastures in almost every square mile of the farming district, and a
cross-country flight from Rantoul to Chicago could have no terrors for
the beginner as regards the choice of a landing ground.
When it comes to a cross-country flight like Ruth Law’s, from Chicago
to New York, these favorable conditions begin to disappear after
the middle of the journey, that is, east of Buffalo. The most ideal
condition for cross-country flying would be one like that on the
London-Edinburgh route, where landing grounds are so frequent that by
flying at a height of a couple of miles the pilot can free his mind
completely of the worry of suitable landing places; but in the United
States we have very few established airdromes, and the only approach
to the London-Edinburgh route is the St. Louis-New York route, where
the jumps are approximately 150 miles; namely, St. Louis, Champaign,
Indianapolis, Dayton, Sandusky, Erie, Hammondsport, Philadelphia, and
New York. That is why long cross-country trips are such an adventure in
this country and such an ordinary affair in England.
The beginner will have special difficulty in training his mind to pick
out available landing places; first of all because the earth looks so
different from the sky that it is only with practice a beginner learns
the shades and hues of color which mean certain kinds of ground, or
learns to spot the different features of flat and hilly country. Even
for an accomplished pilot it is hard to tell whether a field is good or
bad from a height of over 1000 ft.; and as it is dangerous to fly this
low over unknown territory, you can at once see what is meant by the
worry of scanning the countryside for available fields.
Choose the best field that you can get, having a smooth surface
and being easy to get out of in all directions. The following
considerations are intended as a guide to what constitute the best
field, in case you have a choice between several possibilities.
1. Choose a field near a town if possible, or failing that, near a main
road or at least a good road. Remember that a field which appears to
be near a town from the air may actually turn out to be a long walk
after you have landed there and find that there are various trips to be
made to and fro between your chosen landing spot and the town for the
purpose of securing ropes, gasoline, supplies, etc. If you land near a
main road there will probably be telegraph wires along it, which are
undesirable in the case of a small field and wind direction such that
you have to rise off the field over the telegraph wires. It is often
hard to distinguish between main roads and minor roads, and it will
be wise to look for the number of vehicles on any road in determining
whether or not it is the main road.
2. The best field is a stubble field, and is most numerous of course
in the fall when the crops are in. It will have a lightish brown color
when seen from a height, and is pretty sure to be smooth, without
ditches or mounds. Grass land is next best, but is often full of
mounds. Plowed, furrow fields are to be avoided. It might be said that
stubble fields will be hard to get out of after a wet night. Vegetable
and corn fields have a dark green appearance which the pilot must learn
to distinguish from grass pastures, etc. If you choose pasture land,
remember that in summer evenings the farm animals will generally be
lying down near the hedges.
3. Avoid river valleys for landing over night, as there is liable to be
a fog in the morning.
4. Any field which has been previously used for landing with success by
an army officer can be wisely chosen.
The final determination of landing field characteristics can be made
when your airplane has descended to a height of 1000 ft. off the
ground, and in case you are not making a forced landing and your engine
is still going, you can check up your estimate by descending to this
level.
=Proper Dimensions of Fields and Airdromes.=—There are three kinds
of flying fields. One is the airdrome which is used exclusively for
flying, and may be as large as a mile square; very few of these will be
found in cross-country flights in the United States. Second, there is
what is called the “one-way” field, a long, narrow, open space which
is usable when the wind blows parallel to its length. Third, there
is the “two-way” field, which has two sufficiently long runways at
right angles to each other. A two-way field is very much better than a
one-way field, inasmuch as you can always head within 45° of the wind,
whereas in a one-way field an extreme case would be 90°. Moreover,
two-way fields, such as the crescent-shaped field at Dayton, Ohio,
sometimes permit of almost universal direction of flight. The two-way
field may be crescent-shaped, T-shaped, or L-shaped. An L-shaped field
should have each arm 200 by 300 yd. Under certain conditions there may
be buildings located inside or outside the angle which do no harm aside
from creating eddies in case of strong wind. A T-shaped field should
also have its arms 300 by 200 yd. in size.
Regarding the size of fields it can be said that, while the JN-4
machine will rise off the ground after a run of 100 yd. or so, a field
of this length is of course not big enough for frequent use, especially
if bordered by trees, telegraph lines, fences, and so forth. A field
for temporary use should be at least 200 by 200 yd., about 9 acres.
If obstructions at the edges are more than 5 ft. high add to this 200
yd. a distance equal to twelve times the height of the obstruction.
For a permanent field 300 yd. is the minimum dimension necessary for
clearing obstacles and must be increased if the trees exceed 50 ft. in
height. This minimum dimension assumes hard ground and the possibility
of starting in any direction. Training fields are ½ mile square or more.
Whatever field is used either temporarily or permanently by the pilot
should be absolutely familiar to him over every inch of its surface.
The adjacent country should also be absolutely familiar to him from
the standpoint of possible forced landings which he may have to make
during his flight; he should make a habit of informing himself as to
all the woods and hills, etc., which can affect air currents in the
neighborhood of the field from which he is going to start.
=Guide Posts on Airdromes.=—Some fields have pot holes in them, and
these holes should be marked in each case with a large high red or
yellow flag. Do not use short, small flags, as they will frequently be
invisible to pilots taxying on the ground. All telephone wires, etc.,
should have large blankets or other suitable signals hung over them to
warn the pilot away.
Commonly accepted marks for designating a landing spot on airdromes are
as follows:
For day use a large letter “T” lying on the ground, made out of white
cloth strips 15 by 3 ft. This letter T is shifted with the wind so
that its long leg always points in the direction of the wind and the
pilot will therefore have nothing to do in landing but approach the
letter “T” from the bottom, so to speak.
For night flying a system of four flares is used, so arranged that the
pilot in making a proper landing will pass flare A on his left; within
50 yd. further on, flare B; then 100 yd. further on, flare C, also on
his left. In passing flare C he will have a fourth flare, D, 50 yd. to
his right. That is to say, the four flares make the outline of a letter
“L” and the pilot approaches the letter having the long leg on his
left. The flares may be made by putting half a gallon of gasoline into
a pail. This will burn for 30 min. and will be visible 8 miles away.
Sometimes at night instead of flares white sheets can be spread on the
ground and a shaded lamp used to illuminate the sheets.
All searchlights on the landing field should point in the direction
of landing. All other lights within a distance of a mile should be
extinguished, and red lamps should be used at danger points.
On moonlight nights the same signals and guides may be used as in the
daytime.
=Pegging Down an Airplane.=—In landing for the night do not stay up
until it gets dark but choose a landing place which will allow you to
come down 1 hr. before dark; this amount of time will be needed for
laying up the machine over night. As you come to the landing ground
note the time so that you can compute the actual duration of your
flight in your report, then make a good landing. Taxy the machine to
the spot where you intend to leave it over night, such as the lee of
a hedge, etc.; or if there is no choice of position taxy the machine
to the approximate location from which you will make your start next
morning; this will save trouble when you get ready to start.
Dismount from your machine, lift up the tail enough to leave the wings
edgewise to the wind, the machine, of course, facing the wind, and jack
up the tail in this position by the use of any convenient prop. Lash
the control wheel or joy stick fast in a fixed position so that the
wind can not flap the control surfaces around and damage them.
Choose a sunken trench if possible in which the wheels may be sunk;
if the wind is going to blow and there is no sunken trench it will be
wise to dig one so that the effect of the wind on the airplane will be
lessened. If the trench is not necessary, at least put chocks under
the wheels. Peg down the wings and the tail to stakes driven into the
ground using rope if you can get some or lacking this in an emergency
fence wires which you can secure by means of your wire cutters. Do not
lash tightly enough to induce strains in the framework of the machine.
Next, fill up the tanks if a supply of gasoline or oil is available.
Put the covers on the propellers, engine, cowls, etc., in order that
rain and dew shall do no damage to these parts. The wings and body
are varnished waterproof and will not be seriously damaged by a little
moisture; to avoid the collection of moisture in the wings small eyelet
holes are sometimes set in the wings at the trailing edge to let out
the water.
Of course, you will engage a guard to watch the machine all night; see
that a rope is strung around the airplane to keep off the crowd which
may collect.
AERIAL NAVIGATION
=Effect of Wind.=—Navigating in an airplane is complicated only on
account of the fact that there is a wind blowing which may not be in
the desired direction. While on the sea navigation is simple through
the assistance of the magnetic compass (because side winds can not
materially drift the ship sideways), in the air this is not the case;
for if the pilot using the compass points the nose of the airplane
directly north while a west wind is blowing, this wind will cause the
machine to drift in an easterly direction so that in an hour of flight
the airplane will be off its course by an amount equal to distance
which the wind travels in 1 hr.; and the joint result of the motion of
the airplane forward and the motion of the wind sideways will cause
the machine to drift in a northeasterly direction at a speed quite
different from its rated velocity, and in this case somewhat larger.
Victor Carlstrom in his Chicago-New York flight found while he was over
Cleveland that a side wind was deviating his course 17° away from what
it should be, and if he had not had such landmarks as the shore of Lake
Erie for guidance he might easily have lost considerable time.
The question of making allowance for this wind drift is very important
where there are no landmarks, as in the case of night flying, flying
over the sea, or flying over the clouds; and the only way the pilot can
make allowances for these conditions is to figure them out before he
starts from the airdrome, and plan to circumvent them. That is to say,
the pilot in flight has no means, aside from visual observation of the
ground, to determine whether or not the wind is blowing him off his
course. He must determine the whole situation before he starts, and the
process of doing so is as follows.
=Graphical Method for Determining Direction to Steer.=—The pilot will
ascertain from the weather vane and anemometer of the airdrome (1)
the velocity and (2) the direction of the wind, (3) the speed of the
airplane he is to fly, (4) the compass bearing of the actual course
which he desires to follow. With this data it is possible to construct
a simple diagram and to determine the direction to be steered and
the actual velocity which will result in the proposed journey. A
draftsman’s scale, protractor and dividers, a pencil and a piece of
paper are the necessary equipment.
When the wind blows at an angle with the desired course it is necessary
to steer the airplane in such a direction that its own forward motion
will neutralizer the side effect of the drift of the wind from moment
to moment. The problem is to determine this direction for steering, as
it is not known. We are not concerned with distances in this problem,
for the direction is going to be the same whether our flight is of 100
or 200 miles. We are, however, vitally concerned with velocities; and
we will assume that the velocity of the airplane is known to be 75
miles per hour, and from observation on a local anemometer the velocity
of the wind is known to be 20 miles an hour. We also know, of course,
the direction of the wind, which should be given in terms of an angle
whose other leg points directly north. Now if the flight is to be made
at a height of 2000 ft., as is usual in cross-country flight over
average country, we will find that the speed of wind will increase as
we rise up; moreover, that its direction will change. In the present
case the wind will be 88 per cent. higher in 2000 ft. than it is on
the ground; that is to say, the velocity at the altitude we are going
to use is twenty times 1.88, or about 38 miles per hour. Moreover,
as the height increases the direction of the wind changes, shifting
around always in a clockwise direction as the height increases, in the
present case shifting around 16° from its ground direction. (The change
of velocity and direction for various heights is indicated on the
subjoined table.) Thus a west wind becomes at a height of 2000 ft. a
slightly northwest wind, or, to be exact, blows from a direction which
is 74° west of north.
Our treatment of the problem then has for starting points: velocity
of wind, 38 miles per hour; direction of the wind, 74° west of north;
velocity of airplane 75 miles per hour; desired direction of flight
(which has been determined by laying out on the map and reading the
compass bearing with the protractor), say 60° east of north. In 1 hr.
of flight the machine would travel in this unknown direction a distance
of 75 miles were it not for the wind, but for every hour of such flying
the wind is blowing it 38 miles sideways; and the desired direction
must be such that its joint effect, together with the 38 mile sideways
wind, will leave the machine exactly on its proper course at the end of
the hour.
On the map or piece of paper denote the starting point by _A_ (see Fig.
37). From _A_ draw a line parallel to the wind (that is to say, 74°
west of north), and let this line represent, to any convenient scale,
the speed of the wind, 38 miles per hour. The far end of the line may
be called _B_, and may be given an arrow to represent the direction of
wind. Now draw on the map a line from _A_ to the desired destination
(_C_), giving it, of course the proper compass bearing. Take the
dividers, and with _B_ as a center, describe an arc at such distance
as to represent 75 miles per hour, the speed of the machine; this arc
will intercept the line _AC_ at _D_, and _BD_ then gives the direction
to steer, for it is that direction which will permit the airplane in
1 hour exactly to neutralize the sidewise drift of the wind. The
distance _AD_ on this diagram can be measured off and will give the
actual velocity of movement along the line of flight in miles per hour.
Notice that it is 97 miles per hour, quite different from the speed of
the airplane.
[Illustration: FIG. 37.—Graphical method for determining direction to
steer to counteract wind-drift.]
Assuming that the pilot has determined the proper angle toward
which the airplane nose must be pointed, has maintained this angle
throughout his flight by means of the compass and has safely reached
his objective; for the return trip this diagram must be completely
reconstructed (unless the wind is exactly parallel to his course). The
pilot should not make the mistake in returning to the starting point
of steering the airplane nose in a direction exactly opposite to the
outward trip; the reader may make this clear to himself by drawing the
return diagram and comparing it with the outward-bound diagram.
To summarize flying when a cross wind is blowing, it will be said that
the direction of actual travel will not be the direction indicated by
the axis of the airplane; and that therefore while in a picture of the
situation the airplane appears to skid sideways along the whole course
it must be borne in mind that actually there is no skidding whatever
but the air is meeting the airplane in normal manner. The situation
is analogous to that of a fly going from one side to the other of the
cabin of a moving ship, where the actual course through space of the
fly is an apparent skid, due to the resultant of its own and the ship’s
movement.
VARIATION OF VELOCITY AND DIRECTION WITH HEIGHT
(25 miles per hour wind)
————————————————+——————————+—————+——————+——————+——————+——————+—————
Height in feet |At surface| 500 | 1000 | 2000 | 3000 | 4000 | 5000
————————————————+——————————+—————+——————+——————+——————+——————+—————
Velocity change | | | | | | |
in per cent | 100 | 135 | 172 | 188 | 196 | 200 | 200
————————————————+——————————+—————+——————+——————+——————+——————+—————
Clockwise | | | | | | |
deviation | | | | | | |
in degrees | 0 | 5 | 10 | 16 | 19 | 20 | 21
————————————————+——————————+—————+——————+——————+——————+——————+—————
=Effect of Wind on Radius of Action.=—Not only is the direction of
flight altered by the wind but also the radius of action from a
standpoint of gasoline capacity is altered. In the above machine the
gasoline capacity is sufficient for 3½ hr. of flight. How far can it
go across country and return before the gasoline is used up? Always
allow ½ hr. gasoline for climbing and for margin; this leaves 3 hr.,
which at 75 miles an hour is 225 miles, or 112 miles out and 112 miles
back. Now suppose that a flight is to be made across country directly
in the teeth of a 40-mile wind; the radius of flight will be altered as
indicated by the following calculation: Speed outward is obviously 75
minus 40 or 35 miles per hour. Speed on the return trip is obviously 75
plus 40 or 115 miles per hour—3.29 times as fast—and occupying a time
which may be designated by the letter _x_. The time on the outward trip
may be designated by 3.29_x_, a total time of _x_ + 3.29_x_ which we
know equals 180 min. before the gas runs out. Solve the equation _x_ +
3.29_x_ = 180 and we find that _x_ is equal to 42 min., that is, the
return trip requires 42 min., and the outward trip requires 138 min.
The distance covered on the outward trip is then 138/60 of 35, which
equals 80.5 miles. The radius is then reduced from 112 miles to 80.5
miles.
In cases where the wind is not parallel to the line of flight the
actual velocity of course can not be obtained by adding up the airplane
and wind velocities, but must be obtained by the graphical method
mentioned above; thenceforward the calculation is the same.
=Effect of Height.=—Of course if one has to fly in the teeth of a wind
and can choose one’s own altitude, it is desirable to fly low where the
head wind has its smaller velocity, and when flying with the following
wind to rise to considerable altitudes. The proper height at which
to fly will be about 1500 to 3000 ft., for cross-country trips over
ordinary country; but may be increased when the wind is unsteady or
decreased when there are low-lying clouds. The steadiness as well as
the speed of the wind increases with the height. The character of the
country should be carefully investigated from the profile maps before
starting; all hilly parts should be marked on the map as a warning
against landing. Contour is not readily distinguished from a height of
2000 ft. and for this reason points may be indicated on the map where
poor landing places make it desirable to fly high. The character of
the country or the scarcity of landing places may make it advisable to
fly at high altitudes for the following reasons: (1) in case of engine
failure a good margin of height is necessary to provide length of glide
to reach distant landing places; (2) there is then plenty of space for
righting the airplane in case of bumps, side slips, etc.; (3) eddies
or local currents due to inequalities of the ground do not exist to
great heights; (4) landmarks can be better distinguished from high
altitudes because the vision is better (however, one must never trust
to landmarks only in navigating but should constantly use a compass if
only as a check, and especially in passing through clouds). Having
selected in advance the proper height to use during the trip climb to
this height in circles; note the direction of wind drift meanwhile
to check up your estimate. Pass directly over the point of departure
and when over it point the nose of the airplane for a moment directly
toward the desired objective (which can be done with the aid of the
magnetic compass); select some distant object which is dead ahead, and
therefore directly in the course; then head the nose of the machine
up into the wind just enough so that the direction of movement will
be straight toward this distant object. The direction of the nose of
the machine thus set by a method distinct from the graphical method
above mentioned should exactly correspond, however, with the calculated
direction; and thus a means of checking is obtained.
=Effect of Fog.=—The effect of fog upon navigating an airplane is that
it prevents the use of landmarks in aiding the pilot; also that it
upsets the pilot’s sense of level. These two effects are, of course,
independent of the fact that proper landing places are obscured, with
resultant peril in case of engine failure. Therefore, a fog should
be avoided whenever possible; when one comes up, the airplane should
descend, and should never attempt to get above it, as in certain
localities it may turn out to be a ground fog. If the fog is very
bad, land at the earliest opportunity. It is on account of fog that
the pilot avoids river valleys where frequently there is a haze from
the ground up to a height of 700 ft., preventing the view of proper
landing places in case of necessity.
=Effect of Clouds on Navigation.=—Flying in or above the clouds is a
similar case, inasmuch as landmarks can not be seen. It is not wise
to go above the clouds when on the sea coast, as offshore winds may,
unknown to the pilot, carry him out to sea; and any flight over the sea
which is to a distance greater than the safe return gliding distance
is, of course, perilous.
=Navigation by Means of the Drift Indicator.=—The drift indicator is
an instrument for determining directly the side drift of an airplane.
It enables the pilot by looking through a telescope at the ground to
determine exactly what his direction of motion is with relation to the
ground. The telescope is mounted vertically and is rotatable about
its own axis; it has a cross-hair which appears in the field of view
during the pilot’s observation of the ground. As the airplane speeds
overhead objects on the ground will appear through the telescope to
slip backward in the given direction; and when accustomed to the
use of this instrument the pilot can rotate the telescope until the
cross-hair is exactly parallel to the apparent line of motion of
objects on the ground. The telescope cross-hair is parallel to the axis
of the airplane normally and the scale attached to the telescope will
in this case read zero. When the pilot rotates the telescope so that
the cross-hair becomes parallel to the relative backward motion of the
ground the scale will read something different from zero and will
give the angle between the actual line of motion and the axis of the
airplane.
Such a drift indicator is, of course, useful only when the ground is
visible. The pilot knowing the angle between the airplane axis and the
line of motion and therefore knowing the deviation between the supposed
course and the actual course is able to make corrections and steer
the machine in its proper direction. This may be done by altering the
“lubber-line” or his compass just enough to offset the side drift of
the machine; after which the desired course may be followed by simply
keeping to the proper compass bearing. An instrument has been devised
wherein the rotation of the drift-indicator telescope simultaneously
alters the lubber-line zero. The operator then has merely to take
an occasional observation of the apparent drift line of the ground,
which observation automatically shifts the lubber-line and navigation
proceeds as if there were no side wind blowing whatever. Knowing the
angle between the direction of movement and the airplane axis, the
pilot may then compute the speed of motion in a manner analogous to the
graphical method previously mentioned; or he can make use of a chart
for the determination of this speed.
=Navigation over Water.=—In flying over water the presence of waves is
a valuable guide to the aviator, for he knows that these waves extend
in a direction normal to the wind. Moreover, he knows that the velocity
of the waves bears some relation to the velocity of the wind. In order
to estimate the velocity of the waves it is only necessary to know
their wave length, that is, the distance between two consecutive wave
crests. The rule is that for a wave length of 10 ft. the velocity is 10
miles per hour, and will vary as the square root of this wave length;
that is, if the wave length is half, the velocity will be 10 divided by
the square root of 2, or 7.1 miles per hour.
CHAPTER VI
THE RIGGING OF AIRPLANES
=Object.=—The object of this chapter is to teach the elementary
principles of correct rigging. It is not expected that the student
will become an expert mechanic, but with this treatment as a basis and
through practice he will be able to judge whether or not a machine is
correctly and safely rigged. In other words, he will not have to depend
on someone else’s judgment as to whether panels, wires, controls,
struts, etc., of a machine are in good order, but he will be able to
observe understandingly that they are. If the engine goes wrong he can
land, if the rigging goes wrong he is in great difficulty. Moreover, if
the rigging is wrong, speed is lessened and the stability is uncertain.
The first thing to be learned in rigging is a knowledge of the peculiar
terms which have come into use in aeronautics defining different parts
of the machines. Our present list of terms is derived, partly from
French, partly from English, and partly from American terms. Thus
different names may refer to the same part.
NOMENCLATURE
=1. Tractor.=—An airplane that is pulled through the air by a propeller
situated in front of the machine, is called a tractor.
=2. Pusher.=—If the propeller is back of the main lifting planes the
machine is called a pusher.
=3. Fuselage= or =Body=.—The main body of the airplane in which
the pilot sits and to which the landing gear, motor, controls, and
sustaining surfaces are fixed. A small body, especially in pusher types
of machines, is called a Nacelle.
=4. Cockpit.=—The openings and space in the fuselage where pilot or
observer sits.
=5. Stream-line Body.=—The shape of a body or part which permits a
regular flow of air around and along it with the least resistance, in
other words with minimum, obstruction and eddying.
=6. Fairing.=—Building up a member or part of the plane with a false
piece that it may have a stream-line body.
=7. Wings, Planes, Panels.=—The main supporting surfaces of an airplane
are called wings, although the terms planes and panels are probably
as frequently used and even preferred by many. The term panel refers
properly to a section of the wings with the included struts and wires.
The small panel directly above the body is called the engine section
panel or the center panel, while the panels to the right and left of
the body or fuselage are called the main panels. The main panels are
the right and left panels as seen from the seat. Each main panel may
be subdivided into the inner wing bay, the outer wing bay, and the
overhang.
=8. Landing Gear, Chassis or Undercarriage.=—The wheels and the struts
and wires by which they are attached to the fuselage.
=9. Horizontal Stabilizer or Horizontal Fin.=—The horizontal fixed tail
plane.
=10. Vertical Stabilizer or Vertical Fin.=—The small vertical fixed
plane in front of the rudder.
=11. Rudder.=—The hinged surface used to control the direction of the
aircraft in the horizontal plane. As with a boat, for steering or
“yawing” or changing its direction of travel.
=12. Elevator or Flap; Flippers.=—A hinged horizontal surface for
controlling the airplane up and down, usually attached to the fixed
tail plane; for pitching the machine or “nosing up” and “nosing down.”
=13. Tail or “Empennages.”=—A general name sometimes applied to the
tail surfaces of a machine.
=14. Mast or Cabane.=—The small vertical strut on top of the upper
plane used for bracing the overhang.
=15. Ailerons.=—Movable auxiliary surfaces used for the control of
rolling or banking motion. Other definitions are that they are for the
lateral control or for maintaining equilibrium. When they are a part of
the upper plane they are sometimes called wing flaps.
=16. Landing Wires or Ground Wires (Single).=—The single wires which
support the weight of the panels when landing or on the ground.
=17. Flying Wires, or Load Wires (Double).=—The wires which support the
body or fuselage from the planes when in flight.
=18. Drift Wires.=—The horizontal wires which lead from the nose of the
fuselage to the wings and thus keep them from collapsing backward. For
the same reason the wings have interior drift wires.
=19. Diagonal Wires.=—Any inclined bracing wires.
=20. Skids.=—(_a_) _Tail Skid._—The flexible support under the tail of
the machine.
(_b_) _Wing Skid._—The protection under the outer edge of the lower
wing.
(_c_) _Chassis Skids._—Skids sometimes placed in front of the landing
gear.
=21. Horns, or Control Braces.=—The steel struts on the controls to
which the control wires are attached.
=22. Struts; Wing Struts.=—The vertical members of the wing trusses of
a biplane, used to take pressure or compression, whereas the wires of
the trusses are used to take pull or tension. There are also fuselage
struts and chassis struts.
=23. Spar or Wing Bars.=—The longitudinal members of the interior wing
framework.
=24. Rib (Wing).=—The members of the interior wing framework transverse
to the spars.
=25. The Longerons or Longitudinals.=—The fore and aft or lengthwise
members of the framing of the fuselage, usually continuous across a
number of points of support.
=26. Engine (Right and Left Hand).=—In the ordinary tractor machine,
when viewed from the pilot’s seat a right-handed engine revolves
clockwise and right-handed.
=27. Propeller.=—
=28. Pitch (Propeller).=—The distance forward that the propeller would
travel in one revolution, if there were no slip, that is, if it were
moving in a thread cut at the same inclination as the blade. Pitch
angle refers to the angle of inclination of the propeller blade.
=29. Slip.=—Slip is the difference between the actual travel forward of
a screw propeller in one revolution and its pitch.
=30. Dope.=—A general term applied to the material used in treating
the cloth surface of airplane members to increase strength, produce
tautness, and act as a filler to maintain air and moisture tightness.
Usually of the cellulose type.
=31. Controls.=—Since there are three axes or main directions about
which an airplane may turn or rotate it follows that three controlling
devices are required. These are: (1) the elevator for pitching; (2) the
rudder for steering or yawing; (3) the ailerons for lateral, rolling or
banking control.
The term controls is a general term used to distinguish the means
provided for operating the devices used to control speed, direction of
flight and attitude of the aircraft.
=32. Cotter Pins.=—Must be on every nut.
=33. Castelled Nuts.=—Admit cotter pins.
=34. Turnbuckles.=—Must be well and evenly threaded and locked with
safety wires.
=35. Safety Wires.=—For locking turnbuckles and hinge pins.
=36. Shackle and Pin.=—
=37. Hinge Connections.=—
=38. Leading Edge or Entering Edge.=—The front edge of a plane.
=39. Trailing Edge.=—The rear edge of a plane.
=40. Stagger.=—The horizontal distance that the entering edge of the
upper wing of a biplane is ahead of the entering edge of the lower wing.
=41. Dihedral Angle.=—A term used to denote that the wings are arranged
to incline slightly upward from the body toward their tips. The angle
made with the horizontal by this inclination of the wing is called the
dihedral angle.
=42. Angle of Incidence.=—The angle at which a wing is inclined to the
line of flight.
=43. Decalage.=—Difference in angle of incidence between any two
distinct aerofoils on an airplane.
=44. Chord.=—Distance between the entering edge and trailing edge of a
wing measured on a straight line touching front and rear bottom points
of a wing.
=45. Camber.=—The depth of the curve given to a sustaining surface such
as a wing. Thus it will be observed that the planes are not straight
in cross-section but are concave slightly upward. The depth of this
concavity is the camber. Another way of expressing this is that camber
is the greatest distance between the surface of a wing and its chord
line.
=46. Gap.=—The distance between the lower and upper wings of a biplane.
=47. Spread.=—The distance over all from one wing tip to the other wing
tip.
=48. Aerofoil.=—A general name applied to any wing or lifting surface
of an airplane.
=49. Deadhead Resistance.=—Each part of an airplane against which the
wind strikes offers a resistance against being moved through the air.
This is called the _deadhead resistance_ or the _parasite resistance_.
It is for the purpose of lessening this resistance that the parts of a
machine are stream-lined. Remember that force or power must be applied
to overcome this resistance and the lessening of such resistance
decreases the power necessary. A parallel illustration is to think of
the power necessary to push a board sideways through water.
=50. Drift.=—When the air strikes the inclined wing of an airplane its
force has two components. One part called the _lift_ (see 52) acts up
and tends to lift the machine. The other part, called _drift_, tends to
push the machine backward. This drift must also be overcome by applying
power enough to drive the machine forward.
=51. Total Resistance.=—Sometimes called _drag_. (49) Deadhead
resistance added to (50) drift, gives the total forces opposing the
forward movement of the airplane. This is called the total resistance
and is overcome by the _thrust_ of the propeller.
=52. Lift.=—(See 50). The upward or vertical part of the air pressure
acting against the wings, and which is utilized to lift or support the
airplane.
=53. Center of Gravity.=—The point of balance of an airplane which may
be otherwise defined as the point through which the mass of an airplane
acts. If the weight is too far forward the machine is nose-heavy.
If the weight is too far behind the center of lift the machine is
tail-heavy.
=54. Aspect Ratio.=—The ratio of span to chord of a wing or any other
aerofoil.
=55. Gliding Angle (Volplane).=—The angle made to the horizontal by
the flight path of an airplane with the engine shut off; _e.g._, an
airplane is 1000 ft. high, when its engine fails. Suppose its gliding
angle is 1 in 6. Therefore, in still air it can glide 6000 ft. forward.
The general term glide refers to flying without power.
=56. The Angle of Best Climb.=—The steepest angle at which an airplane
can climb.
=57. Stability.=—The property of an airplane to maintain its direction
and to return easily to its equilibrium or balance with a minimum of
oscillation. This is sometimes called dynamical stability. An airplane
may have (first) inherent stability, which is the stability due to
the arrangement and disposition of its fixed parts. It may also have
stability with regard to any one of the three directions in which it
may move. These are named as follows: (1) directional stability, with
reference to the vertical axis; (2) lateral stability with reference to
the longitudinal (or fore and aft) axis; (3) longitudinal stability,
stability with reference to the lateral (or thwartship) axis.
=58. Flying Position.=—Refers to the position of the fuselage when
flying. With the Curtiss JN-4 machines in this position the top
longerons are horizontal and level both ways. The engine bearers are
also level, and the wings have an angle of incidence of 2°.
=59. Capacity.=—The weight an airplane will carry in excess of the
dead load (dead load includes structure power plant and essential
accessories).
=60. Flight Path.=—The path of the center of gravity of an aircraft
with reference to the air.
=61. Stalling.=—A term describing the condition of an airplane which
from any cause has lost the relative speed necessary for support and
controlling, and referring particularly to angles of incidence greater
than the critical angle.
=62. Sweepback.=—The horizontal angle (if any) that the leading edge of
a machine makes with the crosswise or lateral axis of an airplane.
=63. Nose Dive or Vol-pique.=—A dangerously steep descent, head on.
CHAPTER VII
MATERIALS OF CONSTRUCTION
The materials of construction for airplanes should be of such material,
size and form as to combine greatest strength and least weight. With
metal parts in particular it may be necessary to substitute less strong
material for the sake of getting non-corrosive qualities, ability
to withstand bending, ductility or ease of bending, etc. With wood,
absence of warping is important as well. The materials which are
considered are the following: wood, steel, including wires; special
metals as aluminum, brass, monel metal, copper, etc., and also linen
and dope.
=Strength of Materials.=—It is important in a general way to understand
the terms used in speaking of strength of materials. Thus we may have
strength in tension, strength in compression, or strength in shearing,
bending and torsion. Some material fitted to take tension will not take
compression, as for example wire; some material, as bolts, are suited
to take shear, etc.
In general all material for airplanes has been carefully tested and no
excess material is used above that necessary to give the machine the
necessary strength.
=Tension.=—This means the strength of a material which enables it to
withstand a pull. Thus wires are used where strength of this kind is
required.
=Compression.=—This refers to strength against a pressure. Wire has no
strength for this purpose, and wood or sometimes steel is used.
=Shearing.=—Refers to strength against cutting off sideways. Thus the
pull on an eyebolt tends to shear the eyebolt, or the side pull on any
bolt or pin tends to shear the pin.
=Bending.=—In bending material the fibres on the outside tend to pull
apart; those on the inside tend to go together. Thus on the outside
we have tension, and on the inside compression. Along the center line
there is neither tension or compression, it is the “neutral axis.”
=Torsion.=—Torsion is a twisting force, such as an engine propeller
shaft receives.
=Testing for Strength.=—If a wire is an inch square in cross-section
and breaks when a load of 150,000 lb. is hung on it, we say that the
strength of the wire is 150,000 per square inch. Smaller wires equally
strong have a strength of 150,000 lb. per square inch also, but they in
themselves will not support a load of 150,000 lb. but only the fraction
of that, according to the fraction of a square inch represented by
their cross-section.
In the same way, a square inch of wood under a compressive load may
break at 5000 lb. If, however, the piece of wood is long in proportion
to its thickness, it will bend easily and support much less weight.
For example, a perfectly straight walking cane could perhaps have a ton
weight put on it without breaking but if the cane were not set squarely
or if it started to bend it would immediately break under the load.
These cases illustrate the importance of having struts perfectly
straight, not too spindling and evenly bedded in their sockets. Some
training machines are built with a factor of safety of 12. That
is to say, the breaking strength of any part is twelve times the
ordinary load or stress under which the piece is placed. It should be
remembered, however, that under any unusual condition in the air, such
as banking, etc., extra strains are placed on the parts and the factor
of safety is much less than 12. Factor of safety of 12 thus does not
mean exactly what it does in other engineering work, where allowances
are made for severe conditions. The so-called factor of safety of 12 in
airplane work is probably no greater than a factor of safety of 2 or 3
in regular engineering work.
There are three all-important features in the flying machine
construction, viz., lightness, strength and extreme rigidity. Spruce is
the wood generally used for parts when lightness is desired more than
strength, oak, ash, hickory and maple are all stronger, but they are
also considerably heavier, and where the saving of weight is essential,
the difference is largely in favor of the spruce. This will be seen in
the following condensed table of U. S. Government Specifications.
———————————+—————————————+—————————————+————————————
| Weight per | Modulus of | Compression
Wood | cubic foot, | rupture, | strength,
| pounds (15% | pounds per | pounds per
| moisture) | square inch | square inch
———————————+—————————————+—————————————+————————————
Hickory | 50 | 16,300 | 7,300
White Oak | 46 | 12,000 | 5,900
Ash | 40 | 12,700 | 6,000
Walnut | 38 | 11,900 | 6,100
Spruce | 27 | 7,900 | 4,300
White Pine | 29 | 7,600 | 4,800
———————————+—————————————+—————————————+————————————
A frequently asked question is: “Why is not aluminum or some similar
metal, substituted for wood?” Wood, particularly spruce, is preferred
because, weight considered, it is much stronger than aluminum, and this
is the lightest of all metals. In this connection the following table
will be of interest.
————————————————+—————————————+——————————————+————————————————————
| Weight in | Tensile | Compression
Material | cubic feet, | strength per | strength per sq. in
| pounds | sq. in | pounds
| | pounds |
————————————————+—————————————+——————————————+————————————————————
Spruce | 27 | 7,900 | 4,300
Aluminum | 162 | 15,000 | 12,000
Brass (sheet) | 510 | 20,000 | 12,000
Steel (tool) | 490 | 100,000 | 60,000
Nickel steel | 480 | 100,000[1] |
Copper (sheet) | 548 | 30,000 | 40,000
Tobin bronze | | |
(Turnbuckles) | ... | 80,000 |
Monel metal | 540 | 90,000 | 30,000
————————————————+—————————————+——————————————+————————————————————
=Wood.=—Present practice in airplane construction is to use wood for
practically all framing, in other words, for all parts which take
pressure or compression. Although wood is not as strong for its size
as steel and therefore offers more air resistance for the same strength
yet the fact that frame parts must not be too spindling, in other
words, that they must have a certain thickness in proportion to their
unsupported length, has led to the use of wood in spite of the greater
strength of steel. Some airplanes, however, as the Sturtevant, are
constructed with practically a steel framing.
It should be borne in mind that any piece or kind of wood will not
answer for framing, and more especially for repair parts. There is a
tremendous difference in the strength and suitability among different
woods for the work. For instance, a piece of wood of cross or irregular
grain, one with knots, or even one which has been bored or cut or
bruised on the outside, may have only half or less the strength of the
original piece. Air drying doubles the strength of green wood, proper
oven drying is better yet.
Notice how the ends of each piece are ferruled, usually with copper
or tin. This is to prevent the bolt pulling out with the grain of the
wood, and also prevents splitting and end checking and gives a uniform
base on which the pressure comes.
It is generally advised not to paint wood as it tends to conceal
defects from inspection. So varnish only.
Wrapping wooden members with linen or cord tightly and doping this,
both to make waterproof and to still further tighten, increases the
resistance to splitting. The absence of warping tendencies determine
often what wood to choose.
The selection of lumber and detection of flaws is a matter of
experience and should be cultivated. It is, however, nothing more than
the extension of the knowledge that leads a man to pick out a good
baseball bat.
=Woods.=—1. _Spruce._—Should be clear, straight-grained, smooth and
free from knot holes and sap pockets, and carefully kiln-dried or
seasoned. It is about the lightest and for its weight the strongest
wood used. It is ordinarily used as a material for spars, struts,
landing gear, etc., as it has a proper combination of flexibility,
lightness and strength.
2. _White Pine._—A very light wood used for wing ribs, and small struts.
3. _Ash._—Springy, strong in tension, hard and tough, but is
considerably heavier than spruce. Used for longerons, rudder post, etc.
4. _Maple._—Used for small wood details, as for blocks connecting rib
pieces across a spar or for spacers in a built-up rib.
5. _Hard Pine._—Tough and uniform and recommended for long pieces, such
as the wooden braces in the wings.
6. _Walnut, Mahogany, Quarter-sawed Oak._—The strength, uniformity,
hardness and finishing qualities make these woods favorites for
propeller construction.
7. _Cedar Wood._—Is used occasionally for fuselage coverings or for
hull planking in hydroplanes as it is light, uniform and easily worked.
Veneers, or cross-glued thin layers of wood, are sometimes used for
coverings.
Laminated or built-up wooden members have been much used for framing
and for ribs and spars. The engine bearers are always of wood on
account of vibration and are also laminated. In lamination the wooden
strut is built up of several pieces of wood carefully glued together.
The grains of the different layers run in different directions,
consequently a stronger and more uniform stick often is secured. The
objection to laminated pieces comes from the weather causing ungluing.
Laminated pieces should be wrapped in linen or paper and freshened with
paint or varnish from time to time.
=Forms.=—Attention should be called to the hollowed form of many of
the wooden members. In any beam or strut, material at the center of
the cross-section is of far less value in taking the load than the
material away from the center. Therefore, to secure greatest strength
with least weight, it is permissible to lighten wooden members if done
understandingly.
=Steel.=—There is a tremendous difference in the strength, wearing
and other desirable qualities among different steels and irons. For
airplane work none but the best qualities are allowed. For this reason
the use of ordinary iron bolts (as stove bolts) or metal fastenings or
wire not standardized and of known qualities should not be permitted.
The airplane is no stronger than its weakest fitting. This does not
mean that the hardest and strongest steel must necessarily be used, as
ease of working and freedom from brittleness may be just as important
qualities, but the steel on all metal fittings should be of high-grade
uniform stock. A ductile, not too easily bent, mild carbon steel is
usually recommended for all steel plate, clips, sockets and other metal
parts. If any parts are required to be tempered or hardened it must
be remembered that they become brittle and can not afterward be bent
without annealing or softening. Tool or drill steel is a name given to
uniform or rather reliable grades of steel adapted to heat treatment as
tempering or annealing. Often the bolts, clips, nuts, pins, devices and
other fittings are of special heat-treated nickel steel which must not
be heated locally for bending or for attachment. Such work seriously
weakens the steel. The steel is often copper-or nickel-plated and
enamelled to prevent rusting. Do not forget that the proper material
may be twice as strong as other material which looks the same but which
has not received special treatment.
=Wires.=—Only the highest grade of steel wire, strand and cord is
allowable. Manufacturers, as Roebling of Trenton, N. J., manufacture
special aviator wire and cord, which is given the highest possible
combination of strength and toughness, combined with ability to
withstand bending, etc. Steel wire ropes for airplane work are divided
into three classes as follows:
1. _The solid wire_ = 1 wire (as piano-wire grade) and known as
aviation wire.
2. _The strand stay_, consisting either of 7 or 19 wires stranded
together and known as “aviator strand.” Flying and landing wires on
Curtiss.
3. _Cord or Rope Stay._—Seven strands twisted together forming a rope,
each strand being of 7 or 19 wires and known to trade as aviator cord.
The wires are either tinned or galvanized as protection against rust,
etc. Ordinarily galvanizing is used, but hard wires and very small
wires are injured by the heat of galvanizing and they are therefore
tinned.
No. 1. The single wire is the strongest for its weight. Single wires
will not coil easily without kinking and are easily injured by a blow,
therefore their use is confined to the protected parts of the machine
such as brace wires in the fuselage and in the wings.
The strand stay (No. 2) of 7 or 19 wires is generally used for tension
wires, as it is more elastic (can be bent around smaller curve) without
injury, as the flying and landing wires on the Curtiss. The smaller
strands usually have 7 wires, the larger ones 19 wires.
No. 3. _The Tinned Aviator Cord._—The 7 by 19 cord is used for stays on
foreign machines. It is 1¾ times as elastic as a solid wire of the same
material. On the Curtiss it is used for control wires. For steering
gear and controls extra flexible aviator cord is also recommended.
This has a cotton center which gives extra flexibility and is used for
steering gear and controls. It is 2¼ times as elastic as a single wire.
Although wire strands or cords are not quite as strong for the same
size as a single wire they are preferred for general work, being easier
to handle and because a single weak spot in one wire does not seriously
injure the whole strand.
Especial care is necessary to avoid using common steel wires, or
strands which have a frayed or broken wire, or wire that has been
kinked and then straightened or wire that has been locally heated or
wire that has been bruised. All these factors weaken steel rope much
more than is supposed ordinarily.
=Wire Fastening or Terminal Connections.=—Wire terminals are of four
classes:
1. _Ferrule and dip in solder_, then bend back the end. With or without
thimble; used on single wires or on strand; 50 to 94 per cent. as
strong as the wire.
2. _Thimble and End Splicing._—The splice must be long and complete.
Used on cable; 80 to 85 per cent. as strong as the strand; breaks at
last tuck in the splice.
3. _Socket._—Nearly 100 per cent. strong.
4. _End Wrap and Solder._—Simple and serviceable; not used for hard
wire.
Present practice is rather toward elimination of acid and solder,
imperfect bends, flattening of cable on bends, and toward care in
avoiding all injury as kinking to wire, strand and cord due to
unskillful handling of material in the field.
=Other Metals.=—Other metals as aluminum, brass, bronze, copper, monel
metal (copper and nickel) are used for certain airplane fittings for
the reasons of lightness, non-corrosive qualities, or ease of bending,
etc. The trouble with these metals is that they are not uniform and
reliable in strength and in an important part the great strength
combined with minimum weight given by steel is not equalled by any of
these metals. Aluminum is used on the engine hood and also for control
levers and for the backs of the seats. In other words, for parts and
castings which require light metal construction, but which are under
no particular stress. Tin and copper are used for ferrules of wire
joints and for tankage. Copper or brass wire are used for safety wires.
Special Tobin bronze is used for turnbuckles as the part must not only
be strong but free from any tendency to rust. Monel metal (nickel 60
per cent., copper 35 per cent., iron 5 per cent.) is strong and has the
special property of being acid- and rust-resisting. It has been used
for metal fittings and even for wires and for the water jacket of the
motor. Until more strength tests show greater uniformity of strength,
it is to be recommended with caution.
In dealing with metals like steel, it should be remembered that they
are subject to crystallization and fatigue.
Repeated jarring may cause a bar of steel to break easily at a
particular point, when the metal is said to have crystallized there.
Fatigue of a metal may be defined as loss of springiness which may come
from repeated bending and which lessens the strength of metal. Above
all, however, corrosion of steel must be guarded against.
The above points should be clear, as in airplane work you are dealing
with a structure which is safe with perfect materials and workmanship.
The factor of safety, however, is not great enough to permit
carelessness, or defective material.
_Linen._—The almost universal wing covering is fine, unbleached Irish
linen, stretched rather loosely on the wing frames and then treated
with dope.
The linen used weighs 3¾ to 4¾ oz. per square yard, and should have a
strength with the length of the cloth or “warp” of at least 60 lb. per
inch of width. The strength in this direction is slightly greater than
that taken crosswise of the cloth or on the filler or weft. There is a
gain of strength and tautness by varnishing or “doping.”
In general, it is desirable to have wing material which will not sag
easily and have the fabric yield rather than break. This often reduces
stress and saves complete failure.
_Dope._—The linen must be coated with a more or less waterproof dope.
Some form of cellulose acetate or nitrate with more or less softening
material is used and to these some suitable solvent as acetone is
added.
The cellulose acetate or nitrate in the dope acts as a waterproof
sizing, shrinks the cloth tight, and prevents it from changing in
tightness due to moisture. Spar varnish protects this layer from
peeling and makes the wing more waterproof. In service, varnish or dope
must be applied every few weeks.
The U. S. Army practice calls for four coats of cellulose nitrate
dope followed by two coats of spar varnish to prevent inflammability.
Cellulose nitrate is more elastic and durable than the acetate but is
also more inflammable.
Commercial dopes with various desirable properties are: Cellon,
Novavia, Emaillite, Cavaro, Titanine, etc.
FOOTNOTES:
[1] But has very high elastic limit.
CHAPTER VIII
ERECTING AIRPLANES
Airplanes shipped from the manufacturer or from another field almost
always suffer more or less from shipment or packing. Care must be
exercised in unpacking in order not to do any more damage. Boxes should
be placed with the part marked “Top” uppermost. Cables and wires must
be handled carefully in order not to bend or twist them. Every bent or
kinked wire or damaged turnbuckle must be replaced, or at least brought
to the attention of an inspector.
The order of erection is as follows:
1. Assemble landing gear to fuselage and align landing gear before
putting on main panels.
2. Assemble tail.
3. Assemble engine section and align before attaching main panels.
4. Assemble main panels.
1. =Landing Gear Assembly to Fuselage.=—The landing gear is assembled
by mounting the wheels on the axle, and bolting wheels in place. The
fuselage should now be elevated to receive the landing gear. This
may be accomplished in one of two ways—either by tackle or by shims
and blocking. For either method, first connect up the tail skid.
This is accomplished by pinning up the front end of the skid to the
spring-fitting, and then pinning in the other end to the tail-post
socket.
If block and tackle are used to raise the fuselage, pass a line under
the engine-bed supports or sills just to the rear of the radiator.
To this line attach hook of block. =To avoid damaging or crushing
some part do not attach lifting device to any other point.= With the
fuselage now resting on its attached tail skid, lift the front end
until the lower longeron clips clear the landing gear. When the clips
on the longerons line up with the clips on the ends of the struts of
the landing gear the bolts are passed down through the holes thus
aligned. This places the nuts _on the down side_ of the connection thus
facilitating assemblies and inspection of connections. The castellated
nuts are then put on the bolts and drawn up tight, until the drilled
hole in the bolt is visible through the castle of the nut. Then insert
cotter-pin and spread the two leaves backward over the nut. This locks
the nut in place. When the landing gear has been completely assembled
to the fuselage, the tail of the machine should be elevated and
supported by a horse and blocking until the upper longeron is level.
This can be determined by placing a spirit level on the upper longeron
at the tail or on the two engine-bed sills in machines where these
sills are parallel to the top longeron, as in Curtiss JN-4B.
2. =Horizontal Stabilizer.=—After the upper longeron is levelled up,
the horizontal stabilizer is assembled to the tail of the fuselage.
The horizontal stabilizer is fastened by means of bolts in the top
longeron and the tail post. The nuts are all drawn up tight and
cotter-pinned. The vertical stabilizer is next erected in place.
=3. Vertical Stabilizer.=—The vertical stabilizer is now fastened to
the horizontal stabilizer, first by means of the bolt which passes
up through the forward part of the horizontal stabilizer and then by
means of the flexible stay lines running from the top of the vertical
stabilizer. The forward bolt passes through the clip at the lower front
point of the vertical stabilizer. Draw the nuts up tight and lock with
cotter-pins. Flexible wire cables are attached to vertical stabilizer,
and turnbuckles are used to align and tighten cables. The vertical
stabilizer is further aided in its alignment by the bolt clip at its
toe and by the double clip at its heel. This rear double clip passes
over the two bolts which are attached to the tail post and which hold
down the horizontal stabilizer.
=4. Rudder.=—The control braces are first attached to the rudder.
These braces are so placed that the upper tips point toward the hinge
line. In this fashion the holes will match up. The rudder is mounted
on the tail post and vertical stabilizer by means of the hinges. The
hinge pins are inserted in the hinges, and cotter-pins passed through
the drilled holes in the bottom of the pins. The cotter-pins should be
spread backward as usual.
=5. Elevators or Flaps.=—These are first equipped with the control
braces which are also arranged so that the upper tips point toward the
hinge line. The elevators are mounted to the horizontal stabilizer by
means of the hinges and hinge pins. The hinge pins are kept in their
bearings by the cotter-pins, inserted through the drilled holes in the
bottom of the hinge pins.
=6. Panel Assembly.=—The panels are now to be assembled. Before the
main panels can be connected to the fuselage, the engine section panel
must be erected.
_Engine Section Panel._—The engine section struts are first set into
place in their sockets on the engine section. Then the whole thing
is lifted up to place and the four struts are set into their sockets
on the upper longeron. The bracing wires are attached and the engine
section aligned by means of them (see alignment).
=7. Main Panels.=—The main panels are now to be assembled to the
machine. There are two methods for accomplishing this: first, assemble
panels, struts and wires, before attaching to fuselage; second,
assemble the upper plane to the engine section, and complete assembly.
The first method is the most advantageous, since it permits the setting
of the main panels at the correct stagger and dihedral, and does not
require as much adjustment as the second method, which will be omitted.
=Assembling Panels Together Before Fastening Them to Fuselage.=—All the
main struts will be found to bear a number. These numbers run from 1
to 8, on Curtiss JN-4. The numbers on the Standard run from 1 to 12
including the center section struts. The method used in numbering the
posts is as follows: Starting at post No. 1, with the outer post, on
the left-hand side of the pilot, as he faces his direction of travel,
the posts are numbered successively from No. 1 to No. 4; Nos. 1 and 2
being on the left side and Nos. 3 and 4 being on the right side. The
rear posts are similarly numbered from No. 5 to No. 8, Nos. 5 and 6
being on the left and Nos. 7 and 8 being on the right. This system of
numbering does not include the engine section struts. The plan shows
the system graphically (see Fig. 39).
The system of marking also insures that the struts are not inverted
in their sockets. This is accomplished by painting the number on the
strut, so that when viewed from the pilot’s seat, all numbers can
be read, _i.e._, the numbers are painted on that side of the strut
intended to face the fuselage. If a strut is inverted by mistake, it
can thus be quickly detected. The procedure of assembling panels is as
follows:
1. The upper left-wing panel is first equipped with mast, by inserting
the mast into its socket on the upper surface of the wing. The mast
wire is then connected up to the clips to the right and left of the
mast. Adjust the tension in this wire, by means of turnbuckles, until
the spar becomes straight.
2. Stand the upper left-wing panel and lower left-wing panel on their
“leading” or “entering” edges, properly supporting the panels in
cushioned blocks to prevent damage to the nose. Space the panels apart,
at a distance approximately equal to the length of the struts.
3. Next connect up the diagonal cross wires. These must be loosely
connected up, to permit the easy entering of the posts into the
sockets. The wires are connected before the posts or struts are set in
place, since with the latter in place, the connecting of the wires to
the lugs of the sockets is accomplished only with difficulty. After
these wires are thus connected, insert the posts and bolts into place.
4. Connect up closely the “landing” (single) wires, and “flying”
(double) wires of the outer bay to hold the wings together as a unit.
The outer bay is thus completely wired, though but loosely.
5. The posts that are used for this left side are, according to the
diagram, No. 1, No. 2, No. 5, No. 6. No. 1 is the outer front; No. 2 is
the inner front; No. 5 is the outer rear; No. 6 the inner rear.
6. The wings, as above assembled, are now erected to the fuselage.
Extreme care should be exercised in transferring the wings to the
fuselage, not to strain or break them. In carrying the wings, use
wooden boards placed under the wings, and block up under the wing
beams (which can be easily located), so that these take the strain of
the load. Do not attempt handling assembled wings, using the posts
as carriers; or by attachments to the trailing or leading edges. The
wings should be suitably supported temporarily by suitable sling at
the outer upper post point (not beyond this point) or by a horse,
properly blocked under lower wing at outer lower post point (not beyond
this point) during fitting of wing to machine. The wings will have
the approximate stagger if assembled as above, since the posts are
in place, and the tension cross wires are adjusted to almost correct
length when shipped. Insert the hinge pins through the hinges as now
coupled up, lower hinges first.
The machine is now ready for alignment, perhaps the most important of
the rigger’s duties.
=Alignment of Airplanes.=—The proper alignment of a machine largely
determines the flying qualities of that machine.
The alignment of the fuselage should be done at the factory or in the
repair shop. However, the alignment of the whole machine depends upon
the correctness of the fuselage. Directions for aligning and checking
fuselage are, therefore, given.
The order in which the different parts of a machine should be aligned
is as follows:
1. Alignment of landing gear.
2. Alignment of center section.
3. Alignment of leading edge.
4. Getting both wings the same height.
5. Dihedral angle, if any.
6. Alignment of trailing edge (angle of incidence).
7. Stagger.
8. Droop.
9. Tightening and safetying all wires.
10. Length of struts, positions and fittings, warp in planes.
11. Alignment of ailerons.
12. Alignment of stabilizer.
13. Alignment of elevator flaps.
14. Alignment of rudder.
The tail of the machine should be raised until the fuselage is nearly
horizontal before starting the alignment.
=1. Alignment of Landing Gear.=—When a machine is being assembled, it
is easier to align the landing gear before the wings are put on.
Take the weight off the landing gear by supporting the fuselage on
sawhorses.
The axle should be parallel with the lateral axis of the machine.
The center of the axle should be directly under the center of the
fuselage. This can be secured by either of two methods:
(_a_) _By Measuring Cross Distances._—Loosen and tighten the cross
wires until the cross distances are exactly the same. Take all
measurements from similar points on the fittings to which the wires are
attached.
(_b_) _With Level and Plumb Bob._—Level the fuselage crosswise. Mark
the exact center of the fuselage and drop a plumb bob. Mark the exact
center of the axle. Adjust the cross wires until the plumb bob is over
the center of the axle. Tighten the wires until fairly tight, and
safety them.
=2. Alignment of the Center Section.=—When assembling a machine, the
center section should be aligned before the wings are put on.
When a machine is already assembled, the first thing to do is to loosen
all wires except the landing wires. This is very important, for if one
wire is tightened against another wire, an unnecessary and possibly
a dangerous strain may be put upon some member. The bracing wires
connecting tops of center section struts should be tight enough to hold
the shape of the center section when bracing wires are tightened up.
[Illustration: FIG. 38.—Center section and undercarriage alignment.]
(_a_) _Machines Having No Stagger._—In machines having no stagger, the
struts of the center section should be perpendicular to the propeller
axis. As the upper longerons are usually parallel to the propeller
axis, they may be used as a base line.
Align one side of the center section first, then the other side, and
lastly the front.
From a point at the lower end of one of the front center section
struts (the center of a bolt head for example), measure forward on the
longeron a certain distance. From the same point (center of bolt head)
measure back on the longeron exactly the same distance.
Move the upper end of the strut forward or backward by loosening one of
the bracing wires and tightening the other, until the distance from the
two points on the longerons to some point on the center line at the top
of the strut (center of bolt head) are exactly the same. The strut will
then be perpendicular to the propeller axis. Tighten both wires evenly
until fairly tight. Measure the cross distances (the diagonal distances
between similar points at the upper and lower ends of the front and
rear struts), and align the other side of the center section until its
cross distances are the same as those on the opposite side.
Align the front of the center section by loosening one cross wire and
tightening the other, until one cross distance is exactly the same as
the other cross distance.
(_b_) _Machines Having Stagger._—In machines having stagger, the shape
and position of the center section strut fittings usually determines
the amount of stagger the machine was designed to have (Fig. 38-_a_).
The JN-4 has 10⅝-in. stagger, _i.e._, a plumb line dropped from the
leading edge of upper panel should be 10⅝-in. from leading edge of
lower panel.
Adjust the wires on one side of the center section until the struts
and that side are in their correct positions as shown by the shape
of the fittings. Tighten the wires, measure the cross distances, and
adjust the wires on the other side of the center section until the
cross distances are exactly similar to the first set.
A more accurate method is to drop a plumb line from the leading edge of
the center section and adjust until the line is at the correct distance
ahead of the point on the fuselage where the leading edge of the lower
wing meets it. This point may be determined by measuring the distance
from the inside of the front hinge to the leading edge of the lower
wing and then laying off this distance on the body from the front of
the hinge on the lower longeron. Better still, if the hinges are at
the same distance from the leading edge on both top and bottom wings,
the plumb line may be dropped from the front side of the hinge on the
center section and the stagger measured back to the hinge on the lower
longeron (Fig. 38-_b_). This has the advantage of setting the plumb
line out far enough to clear the fuselage. Also the measurements are
easily made.
Next, adjust the two front wires until one cross distance is exactly
the same as the other cross distance (Fig. 38-_c_).
=3. Alignment of Leading Edge.=—(_a_) _Upper Plane._—The leading
edges of the upper and lower planes of one wing should next be made
perfectly straight. By standing on a step ladder, placed 15 to 20 ft.
to one side, and sighting along the leading edge of the upper plane,
any bow or warp can be easily seen. This should be straightened out by
loosening or tightening the front landing wires. The edge should be
brought in exact line with the leading edge of the center section.
(_b_) _Lower Plane._—After the leading edge of the upper plane has been
made straight, sight along the leading edge of the lower plane. If
there is no warp in the plane, this edge should also be straight.
(_c_) _Align the opposite wing in the same manner._
=4. Getting Both Wings the Same Height.=—Place a small tack exactly in
the middle of the leading edge of the center panel.
Measure from this tack to similar points at the lower ends of the
intermediate and outer struts (Fig. 39). Make these distances the
same on each side by raising or lowering one wing or the other, or by
raising one wing and lowering the other wing, all the while keeping the
leading edges of both wings perfectly straight.
=5. Dihedral.=—The method of setting the wings of a machine at a
dihedral angle is as follows:
Place two tacks in the leading edge of the upper plane, one tack near
the tip of each wing and exactly the same distance out from the tack
in the center section. Stretch a string tightly between the two outer
tacks, until there is no sag in the string.
A dihedral angle of 178° means that each wing has been raised 1°. To
set the wings of a machine at a dihedral angle of 178° for example:
(_a_) Find the natural sine of 1° (0.0175).
(_b_) Multiply this by the distance in inches between the center tack
and one of the outer tacks. The result will give the rise, in inches,
of the string over the tack in the center section.
Raise the wings equally, keeping the leading edges perfectly straight,
until the proper rise shows over the center section.
[Illustration: FIG. 39.—Alignment diagrams.]
=6. Alignment of Trailing Edge (Angle of Incidence).=—(_a_) _Lower
Plane._—The trailing edge should be brought parallel to the leading
edge. This can be done by bringing the rear spar in line with the
leading edge.
Stand squarely in front of the center of the machine 15 to 20 ft.
away. Sight under the leading edge of the lower plane; move forward or
backward until the fittings under the rear spar are just visible. Raise
or lower the trailing edge by loosening or tightening the rear landing
wires, until all of the fittings on the rear spar appear equally under
the leading edge.
(_b_) _Upper Plane._—After aligning the trailing edge of the lower
plane, place a ladder in front of the center of the machine, and sight
under the leading edge of the upper plane. If there is no warp in this
plane, the trailing edge should align with the leading edge.
The objection to this method is that since there are no fittings next
the body on the rear spar, there is room for considerable error in the
angle of incidence.
Reversing the process and finding the angle of incidence at each set
of struts secures the alignment of the trailing edge and removes
the liability to error. To set wings at correct angle of incidence
proceed as follows (Fig. 39): Place the airplane in rigging position,
_i.e._, level up the top longeron or engine bearers. Set the corner
of the straight-edge against the center of the rear spar, level up
the straight-edge, and measure from the top of the straight-edge to
the center of the front spar or to the lowest point of the leading
edge. This must be done next the body and under each set of struts.
(It is useless to make such a measurement between the struts because
of possible warping of the wings.) Unless the wings have a washout or
washin the measurements must agree, thus making the angle of incidence
the same all along the wing. Then the trailing edge must necessarily be
parallel to the leading edge.
=7. Stagger.=—The stagger should be the same all along the wing as it
is for the center section. With the machine in rigging position drop a
plumb line from the leading edge of the upper wing in front of each set
of struts. The distance from the plumb line to the lower edge should
equal the stagger. If there is too much, tighten the diagonal wire
running from the lower rear socket to the upper front socket, being
sure that the other diagonal wire is loosened somewhat. For too little
stagger tighten the latter and loosen the former wire.
Check up the dihedral and alignment of the trailing edges to see if
these have been disturbed while setting the stagger. If not, the droop
may be put in.
=8. Droop.=—To correct for the torque of the propeller, one wing of a
machine is slightly drooped.
In single-motored tractor types, if the propeller turns to the right,
when looking from the rear, the left wing is drooped, and _vice versa_.
The outer rear landing wire of the wing to be drooped should be
loosened until the trailing edge, between the outer and intermediate
struts, appears to be about an inch (for machines of not more than 100
hp.) lower than the rest of the trailing edge. The practice with the
Curtiss JN-4B is to loosen the inner rear landing wire on the left
wing ¼ in. and loosen the outer rear landing wire ½ in. after the angle
of incidence and stagger have been adjusted so that corresponding wires
on the right and left wings are the same length.
=9. Tightening and Safetying All Wires.=—(_a_) After the wing is
drooped, all flying wires should be tightened to the same tension, and
just taut enough to take out all sag.
(_b_) Next tighten all drift or cross wires between the front and rear
struts to the same tension.
(_c_) Drift wires from the wings to the fuselage, and from the wings to
the landing gear, if any, should be tightened last.
(_d_) Safety all turnbuckles. A wire too loose will vibrate when the
machine is in the air.
The flying and drift wires should be so tightened that when they take
the weight of the machine in the air, there will be no sag in the
landing wires.
=10. Length of Struts, Positions of Fittings, Warp in Planes.=—The
above instructions are given for machines that are true, that is,
machines having no bends, warps, or bows in the spars and leading or
trailing edges.
(_a_) Similar struts should be of the same length.
(_b_) Similar fittings occupying similar positions should be spaced
the same. If difficulties are encountered in getting the measurements
to tally, check up the lengths of the struts and the positions of the
fittings.
(_c_) If the planes of a machine are warped, the machine should be so
aligned that the warp is equally divided between both planes.
=11. Alignment of Ailerons.=—Before aligning ailerons, place the
shoulder yoke or wheel controlling the ailerons in the center of its
path of movement.
(_a_) _Trailing-edge Ailerons._—Trailing-edge ailerons should be set
¾ inch lower than the trailing edge of the plane to which they are
attached.
(_b_) _Interplane Ailerons._—Interplane ailerons should be set so that
they are both in the same plane, when in neutral position.
In machines having interplane ailerons, nose heaviness and tail
heaviness may be corrected by setting the trailing edges of the
ailerons up or down.
The proper amount to raise or lower the trailing edges can be
determined only by experimenting with each particular type of machine.
(_c_) The control wires should be just tight enough to eliminate any
lost motion.
=12. Alignment of Stabilizer.=—Support the weight of the tail on the
tail skid.
The rear edge of the stabilizer should be perfectly straight, and
should be parallel with lateral axis of the machine.
Stand behind the center of the stabilizer, and align its rear edge on
the leading edge of the upper plane by sighting. Tighten wires and
safety turnbuckles.
=13. Alignment of Elevator Flaps.=—Set the elevator control in its
mid-position. Adjust the elevator control wires until the flaps are in
their neutral position and both are in the same plane. The wires should
be just tight enough to eliminate any lost motion. Safety turnbuckles.
=14. Alignment of Rudder.=—Set the rudder control (wheel, foot pedals,
or foot bar) in its mid-position. Adjust the rudder control wires until
the rudder is in its neutral position. The control wires should be just
tight enough to eliminate any lost motion. Safety the turnbuckles.
=15. General.=—All connections having been made, carefully go over
each shackle, pin, and turnbuckle, and see that all pins are properly
in place, all nuts on bolts tight and all cotter-pinned. Try out all
controls for action and freedom of movement. See that no brace wires
are slack, yet not so taut that when plucked they “sing.”
=16. Overall Adjustments.=—As a final check, the following overall
measurements should be taken (see Fig. 39).
The straight lines _AC_ and _BC_ should be equal to within ⅛ in. The
point _C_ is the center of the propeller, or in the case of the pusher
the center of the nacelle. _A_ and _B_ are points on the main spar
and must be at the same distance from the butt of the spar. They must
not be merely the sockets of the outer struts as these may not be
accurately placed. _AC_ and _BC_ must be taken from both top and bottom
spars; two measurements on each side of the airplane.
Similarly _FD_ and _FE_ should be equal to within ⅛ in. _F_ is the
center of the fuselage or rudder post. _D_ and _E_ are points marked on
both top and bottom rear spars just as _A_ and _B_ were marked on front
spars.
If these measurements are not correct, it is probably due to some of
the drift or antidrift wires being too tight or too slack. These must
then be located and corrected.
WING COVERING AND PATCHING
The wings are covered with best quality Irish linen which must have a
tensile strength of at least 50 lb. per inch width, undoped, and 70 lb.
when doped.
The linen strips are sewed together on a sewing machine in such a way
that when folded together they form a sort of bag which just slips over
the wing frame. The seams then run diagonally across the wing. The
bag is stretched up loosely and tacked temporarily along the leading
edge. The edges are folded under a little and sewed together along the
leading edge of the wing and the temporary tacks are removed. To hold
the covering up to the ribs, thread is looped through from one side
of the panel to the other around the ribs. The rough surfaces made by
the thread along the ribs and the edges are covered over with strips
of linen pasted on with dope. To make a smooth job, the edges of these
strips are frayed out ⅛ in.
Three or more coats of dope are applied and rubbed down after each
coating is dry. This is then covered over with one or two coats of
varnish to make it more weatherproof and smooth. Varnish also prevents
the dope from peeling off.
Dope shrinks the linen and makes it fit up tight to the framework.
Breaks in the fabric are patched by first removing the dope around the
break with dope remover and then sticking on a patch with dope. This
is applied with a rag instead of a brush in order to prevent the patch
from becoming white. Ten to sixteen coats of dope are then applied over
the patch, each coat being allowed to dry before the next is applied.
FAULTS IN FLIGHT, DUE TO IMPROPER ALIGNMENT AND HOW TO CORRECT THEM
An airplane pilot may experience difficulty with the flying
qualities of his machine. Consequently he should know something
about the conditions which are responsible for the various kinds of
unsatisfactory flying qualities which are more or less characteristic
of airplanes.
In the chapter on “Principles of Flight” the reader has been made
acquainted with such terms as stability, instability, longitudinal
stability, etc. For the purposes of rigging, however, it will be well
to review these terms again.
_Stability_ is a condition whereby an object disturbed has a natural
tendency to return to its first and normal position. Example: a weight
suspended by a cord.
_Instability_ is a condition whereby an object disturbed has a natural
tendency to move as far as possible away from its first position, with
no tendency to return. Example: a stick balanced vertically on your
finger.
_Neutral stability_ is a condition whereby an object disturbed has
no tendency to move farther than displaced by the force of the
disturbance, and no tendency to return to its first position.
Now in order that an airplane may be reasonably controllable, it is
necessary for it to possess some degree of stability longitudinally,
laterally and indirectionally.
_Longitudinal stability_ is its stability about an axis transverse to
the direction of normal horizontal flight, and without which it would
pitch and toss.
_Lateral stability_ is its stability about its longitudinal axis, and
without which it would roll sideways.
_Directional stability_ is its stability about its vertical axis, and
without which it would have no tendency to keep its course.
Whenever an airplane does not fly properly, aside from conditions
arising from engine or propeller trouble, either its longitudinal,
lateral, or directional stability is affected. When its longitudinal
stability is affected we call this condition longitudinal instability;
likewise, regarding lateral stability and directional stability,
referring to these conditions respectively as lateral and as
directional instability. The effect of alignment errors will be
treated under the foregoing respective heads.
=Alignment Errors, Longitudinal.=—
1. _The Stagger May Be Wrong._—The top surface or wing may have drifted
back a little owing to some of the wires, probably the incidence
wires, having elongated their loops or having pulled the fittings into
the wood. If the top surface is not staggered forward to the correct
amount, then consequently the whole of its lift is too far back, and it
will then have a tendency to lift up the tail of the machine too much.
The airplane will then be said to be nose-heavy. A ¼-in. error in the
stagger will make a very considerable difference in the longitudinal
stability.
2. _The Angle at Which the Main Surfaces Are Set Relative to the
Fuselage May Be Wrong._—This will have a bad effect especially in the
case of an airplane with a lifting tail plane or horizontal stabilizer.
If the angle of incidence is too great, the machine will have a
tendency to fly “tail-high.” If the angle is too small the airplane may
have a tendency to fly “tail-down.”
3. _The Fuselage May Have Become Warped Upward or Downward._—This would
give the tail plane or horizontal stabilizer an incorrect angle of
incidence. If it has too much angle, it will lift too much, and the
airplane will be “nose-heavy.” If it has too little angle, it will not
lift enough and the airplane will be “tail-heavy.”
4. _The Tail Plane May Be Mounted upon the Fuselage at a Wrong Angle of
Incidence._—If this condition exists, it must be corrected by making a
change at the fittings. If nose-heavy, the tail plane should be given a
smaller angle of incidence. If tail-heavy, it should be given a greater
angle of incidence; but care should be taken not to give it too great
an angle, because the longitudinal stability entirely depends upon the
tail plane being set at a smaller angle of incidence than is the main
surface, and if that difference is decreased too much, the airplane
will become uncontrollable longitudinally. Sometimes the tail plane
is mounted on the airplane at the same angle as the main surface, but
it actually engages the air at a lesser angle, owing to the air being
deflected downward by the main surfaces.
=Alignment Errors, Lateral.=—The machine manifests a tendency to fly
one wing down. The reason for such a condition is a difference in the
lifts of the right and left wings, assuming the motor torque is already
taken care of by washout. That may be caused as follows:
1. _The Angle of Incidence of One Wing May Be Wrong._—If it is too
great, it will produce more lift than on the other side of the
airplane; and if too small, it will produce less lift than on the other
side—with the result, in either case, the airplane will try to fly one
wing down.
2. _Distorted Surfaces._—If some part of the surface is distorted, the
lift will not be the same on both sides of the airplane, which, of
course, will again cause it to fly one wing down.
3. _The Ailerons May Be Set Slightly Wrong._—This may be due to one
control cable being longer than the other, or one of the aileron horns
being bent or twisted. This condition can easily be detected by setting
the aileron control—in neutral and checking up the position of the
ailerons.
=Alignment Errors, Directional.=—If there is more resistance on one
side of the airplane than on the other the airplane will, of course,
tend to turn to the side having the most resistance. This may be caused
by the following conditions:
1. _The Angle of Incidence of the Right and Left Surfaces May Be
Unequal._—The greater the angle of incidence, the greater the
resistance. The less the angle, the less the resistance.
2. _If the Alignment of the Fuselage, Vertical Stabilizer, the Struts
or Stream-line Wires Is Not Absolutely Correct._—That is to say, if
they are turned a little to the right or left instead of being in line
with the direction of flight—then they will act as a rudder and cause
the airplane to turn off its course.
3. _If Any Part of the Surface Is Disturbed It Will Cause the Airplane
to Turn off Its Course._—If, owing to the leading edge, spars, or
trailing edge becoming bent, curvature is spoiled, that will result in
changing the amount of resistance on one side of the airplane, which
will then develop a tendency to turn off its course.
=Additional Flight Defects.=—In addition to the foregoing the following
conditions may also exist which cause trouble when flying as well as
when landing:
_Airplane Climbs Badly._—Such a condition, apart from engine or
propeller trouble, is probably due to excess resistance somewhere.
_Flight Speed Poor._—This condition apart from engine or propeller
trouble, is probably due to (1) distorted surfaces, (2) wrong angle of
incidence, or (3) dirt or mud, resulting in excessive skin friction and
weight.
_Inefficient Control._—This is probably due to (1) wrong setting of the
control surfaces, (2) distortion of control surfaces, or (3) control
cables being badly tensioned.
_Will Not Taxi Straight._—If the airplane is uncontrollable on the
ground it is probably due to (1) alignment of the undercarriage being
wrong, (2) unequal tension of shock absorbers, (3) tires unequally
inflated, (4) axle bent, (5) tight wheel and axle, (6) loose spokes
causing wheel to wobble.
CHAPTER IX
TRUING UP THE FUSELAGE
Before an airplane is assembled for the first time after leaving the
factory, and especially after it has made its first few “breaking-in”
flights, the fuselage or basic framework should be carefully examined
and checked up. This is done in order to determine whether or not the
fuselage became distorted from rough usage during shipment (which is
always likely) or from taking sets due to the flying stresses to which
it was subjected for the first time during the “breaking-in” flights.
It frequently happens that rough landings and “stunt” flying cause
distortions of the fuselage frame and other parts of the airplane so
that it is very necessary to make a careful inspection immediately
after to ascertain not only what twists, bows and stretching of vital
parts have resulted, but also to detect fittings, wires, etc., which
may have been pulled loose or broken. The extreme importance of having
your airplane adjusted correctly and carefully, and to know that it is
in the proper condition can not be reiterated too often. And, since
the fuselage is the foundation from which, so to speak, the entire
apparatus is built up, it is doubly important that it should always be
in correct adjustment.
When the fuselage is built in the factory it is placed on a long table
whose surface is perfectly horizontal and which has metal strips
inlaid. This table in reality is a big face plate especially arranged,
as described, for fuselage truing in the factory. The fuselage, of
course, has had none of its coverings applied when it is placed on the
table, nor are the accessories such as controls and engine in place.
On this table then the builders begin to do the necessary adjusting
and this is no simple or quick job. Working from a perfectly smooth
horizontal surface it is, of course, easy to detect warpings, twists,
etc., of the framework. These are first remedied by tightening or
loosening of cross wires, etc., as the case may be. Then, when the
fuselage is reasonably square and level, lengthwise and crosswise, as
determined by the eye, check measurements are taken by rule, trams and
level and final adjustments made to bring the various parts in final
proper relation to one another. For instance, the rudder post must be
perfectly vertical, as determined by a plumb line, when the engine
bearers or the top longerons are level. The various fittings such as
those for horizontal and vertical stabilizers and the engine sections
and side panels must all conform accurately to one another so that
the airplane as a whole, when it is assembled, will not contain any
inherent defects such as tail planes with slightly distorted angles of
incidence, left main panels ahead of right or over or under right main
panels, fittings so located that an initial strain must be imposed
upon them by forcing them together, etc.
After the fuselage has been lined up in the factory as described
briefly above, it is permitted to set for a week or so and then it is
checked up again and such additional slight corrections made which
would be necessitated by the sets which had occurred. The additional
fittings required are then applied and the fuselage finally covered and
sent away to have the engine and instruments applied.
When checking and truing a fuselage on the flying field after the
airplane has been assembled and flown the process is not quite so
simple as when the fuselage is checked up and trued in the factory,
largely owing to the lack of ideal factory facilities and also because
so many fittings, coverings, etc., are in the way which one must
always be cautious about removing. In general, the method of procedure
may be outlined as follows, but it must be obvious that one can not
in a series of written notes touch upon all the possible queries and
combinations of fuselage distortions which may occur and the ways for
detecting and correcting them. A certain amount of experience in the
field accompanied with some fixed habits of inspection, and everlasting
curiosity about the perfections of your machine, and a willingness and
readiness always to pitch in and help correct the defects found, will
soon develop in you the ability to diagnose easily and quickly and
remedy intelligently whatever trouble you may run across.
For satisfactory fuselage checking and truing let us say in the field
shop, a certain minimum equipment of tools is necessary. This equipment
is:
At least two sawhorses about 3 to 4 ft. high for mounting the fuselage
in flying position.
Several wooden wedges (show taper) for easy adjustment of fuselage for
cross and lengthwise level.
About 25 yd. of strong linen line for checking center lines.
2 carpenter levels about 2 to 3 ft. long.
4 perfectly formed steel cubes about 1¼ to 1½ in. in size.
1 plumb bob.
1 small screw jack.
1 pair of wood clamps.
1 straight edge about 12 ft. long.
Several small Crescent adjustable wrenches.
Several pliers with wire-cutting attachment.
Pins for manipulating turnbuckles.
1 steel tape.
1 foot rule, 6 ft. long.
1 small brass hammer.
A small work bench equipped with a 3-in. or 4-in. vise.
The fuselage which is to be trued is mounted on the horse with the
wedges between the top horse rails and the lower longerons. These
horses or trestles should be so arranged that about three-fourths of
the fuselage toward the tail sticks out unsupported. In this way it
will take, as near as possible, its normal flying position. It is
always desirable, in fact quite necessary, especially when checking
a fuselage for the first time, to have the airplane’s specifications
as well as a detailed drawing of the fuselage and an assembly of the
airplane as a whole available. The reason for this, of course, is
quite obvious.
The engine bearers and the top longerons are the basic parts from
which the fuselage as a whole is lined up. Consequently the first
thing which is done, when inspecting the fuselage for alignment, is
to test the truth of these parts. This is done by sighting the top
longerons lengthwise to see if they are bowed downward, upward, inward
or outward. As near as possible the fuselage is made level on the
trestles. The steel blocks or cubes referred to in the tool list above
are placed on the longerons and the straight edge and level placed on
these, first crosswise and then lengthwise. A string is stretched over
the top of the fuselage touching the top cross braces and brought as
close as possible to the center of these pieces. This string should
stretch from the rudder post as far forward as possible. Then the
cross wires or diagonal brace wires are sighted to see how close their
intersections agree with this center-line string. Furthermore, the
level is placed on the engine bearers and they are tested for cross
level and longitudinal level. If the engine is mounted in place, but
one point on the bearers will be available for this purpose, but the
check should nevertheless be made. It may also be found that the
longitudinal level of the engine bearers can be tested from underneath
by placing the steel cubes mentioned above on the top of the level
and then holding the level up against the bottom of the bearers. As a
rule, if the fuselage is warped it should be possible to detect this
with the eye, but when engine bearers are out of line this can only be
detected with certainty by the use of the level.
Let it be assumed that the fuselage is out of true. The first parts
to tackle are, of course, the engine bearers. If they should not be
in line they must first be brought so, and afterward kept in this
condition. The diagonal wires at the front of the fuselage should be
adjusted to make this correction. If the bearers are badly out of line
it will, perhaps, be wisest to remove the engine, or at least loosen
it up from the bearers before doing any adjusting for the reason that
it may become strained by serious pulling on the bearers. After the
bearers are in place, it will be safe to bolt the engine fast again.
With the engine bearers temporarily disposed of, the fuselage proper is
tackled. Here the first thing to do is to get the top surfaces of the
longerons level crosswise. Use the spirit level and the two steel cubes
mentioned in the tool list for this purpose. Start at the front of the
fuselage in the cock pit. Adjust the internal diagonal wires until the
level bubble is in its proper place. Then measure these first two sets
of diagonal wires, getting them of equal length. Continue this process
throughout the length of the fuselage until the rear end is reached,
always working from the front.
Lastly, before proceeding to the next operation, try the engine bearers
for level again. If out, make the proper adjustments.
If the centers of the crosswise struts are not marked, this should
first be done before going further. Then stretch a string from No.
1 strut, or as far forward as possible to the center of the rudder
post. All center points on the cross struts, if the fuselage is true
lengthwise, should lie exactly on this string. If not, adjust the
horizontal diagonal wires, top and bottom, working from the front,
until the center-line points all agree. Always check by measuring
diagonal wires which are mates. These should be of equal length. If
not, some wire in the series may be overstressed. In order to pull
the center points on the cross struts over, always stop to analyze
the situation carefully, determining which are the long diagonals and
which the short ones from the way the fuselage is bowed. Then shorten
the long ones and ease off on the short ones, being careful never to
overstress any of the wires.
The last thing to do is to bring the longerons or the center line
of the fuselage into level lengthwise. For this purpose a long
straight-edge, the two cubes, and a spirit level are of advantage,
although simply stretching a string closely over the top of the
longeron may suffice. Then as in the case of removing a crosswise
bow in the fuselage, here too, we manipulate the outside up and down
diagonal wires in bringing the top longerons into their proper level
position lengthwise, always working from the front.
After all this is done it is well to make some overall checks with
steel tape or trams to see how various fittings located according to
the drawings, agree with one another. Since there is a right and a
left side, distance between fittings on these sides may be compared.
And, finally, the engine bearers should be tried again. In short no
opportunity should be neglected to prove the truth of the fuselage as a
whole and in detail.
It might be pointed out that an excellent time to check the fuselage is
when engine is being removed or changed. In fact this time in general
is a good one to give the airplane as a whole, a careful inspection.
After all the necessary corrections have been made and all the parts
of the fuselage brought into correct relation with one another, the
turnbuckles are safety wired and then served with tape to act as a
final protection. The linen covering is reapplied if it had previously
to be removed and the level, empennage wires, panels etc., are placed
in position and aligned as pointed out in the notes on assembly and
alignment.
CHAPTER X
HANDLING OF AIRPLANES IN THE FIELD AND AT THE BASES PREVIOUS TO AND
AFTER FLIGHTS
No unimportant part of the operation and maintenance of airplanes
is their handling in the field, and at the various bases previous
to, between, and after flights. This phase of the entire subject
contemplates the transportation of airplanes in knockdown condition
either by railway or truck, their unloading and unpacking, to a certain
extent their assembly, their storage in hangars and sheds, their
storage and disposition in the open, their disassembling and packing
for transportation, etc.
=The Unloading and Unpacking of Airplanes.=—The personnel required to
unload an airplane properly boxed and crated from a railway car, is
15 men and two non-commissioned officers. The tools needed for this
purpose are:
1 ax.
2 crowbars.
6 lengths of iron pipe about 2 in. in diameter, 3 ft. long.
6 lengths of iron pipe about 2 in. in diameter, 4 ft. long.
100 ft. manila rope, 1 in. in diameter.
A regular flat-bed moving truck or ordinary truck with a flat-bed
trailer should be provided for handling the machine from the car to
the field erecting shop.
Airplanes are usually shipped in automobile cars with end doors or
gondola cars. After opening doors of cars, examine and inspect all
crates and boxes carefully to see that they are all there in accordance
with the bill of loading or shipping memorandum, as well as to see that
they are in good condition. If any boxes are found damaged, they should
not be removed from the car without first reporting the fact to the
receiving officer.
Next, all cleats and bracing should be removed. The crate containing
the fuselage and engine should, if possible, be unloaded first. The
heavy end where the engine is fixed should be lifted up, have 2-in.
pipe rollers put underneath and manipulated into the truck which has
been backed up against the car door so that this heavy end, when
finally placed, will rest on the body of the truck as far forward as
possible. Next lash the front end of the box securely to the truck.
Should it happen that the fuselage crate is so located in the car that
the light end must of necessity emerge first through the door, then
this end may be run on to a truck and the crate removed from the car
with the heavy end adequately supported by sufficient help. Another
truck is then backed up against the rear of the first one which has
been moved into the clear, and the heavy end of the fuselage crate
brought to rest as far forward as possible in the second truck. It is
then secured and the first truck released.
After the box is properly lashed by means of the manila rope, a man
should be placed on each side of it to watch and see that the lashings
do not loosen and the box shift in transit. Trucks should be driven
slowly, especially over rough ground, tracks, etc. In addition to the
fuselage crate it may also be possible to load the panel crates on this
same truck, but as a rule it is better to load these on a second truck.
Common sense goes a long way in transporting aircrafts by motor trucks.
Unloading of the crates is done with the use of skids applied to the
rear of the truck and secured so as to form a sort of an inclined plane
down which to slide the boxes on the pipe rollers to the ground. These
skids should be at least 4 in. by 4 in. by 6 ft. and made of strong
wood. The rear end of the crate may be brought to the ground, rested
there, and the truck moved forward slowly until the entire length rests
on the ground. Care must be used not to jolt or drop this box at any
stage whatsoever.
When uncrating the fuselage, remove the top and both ends of the box.
Fold both sides of box flat down on ground and use same for assembling
machine. The wing boxes should have the tops removed and planes lifted
out in that manner.
Next, the airplane is assembled in accordance with instructions already
given.
=The Dismantling and Loading of Airplanes.=—When airplanes are to be
prepared for shipment by motor truck or railway, they should, of
course, be taken down and crated similar to the way they were shipped
from the factory. The order in which this is done should be as follows:
Remove propeller.
Unfasten control wires.
Unfasten main planes from fuselage and dismantle on ground.
Remove tail surfaces.
Unless machine is to be placed in box, landing gear and tail skid
should remain attached to fuselage.
If the machine is crated it should be handled when shipped the same
as described above. If, however, it is to be loaded without being
crated, then the following procedure should be observed. Using two
planks, 2 in. by 12 in. by 18 ft. long for runway from ground into car,
load machine into car, engine first. Block wheels to prevent machine
shifting. Secure fuselage, tail end, to the floor of the car by means
of ropes passed over the fuselage and fastened to the floor with
cleats. The wings should be crated against the sides of car and secured
by wires, ropes or canvas strips. All boxes should be marked with name
of organization, destination, weight, cubic contents, hoisting centers,
number of box, “This Side Up,” etc. A shipping memorandum should always
be made out and mailed to destination when shipment goes forth.
=Storing of Airplanes and Parts at Bases and in Fields.=—Airplanes when
not in active flying duty are stored in hangars or sheds especially
adapted to house them. Under certain conditions it is necessary to
store them in the open. In each case particular precautions should be
observed in order not to subject the machines to unnecessary wear and
tear.
Since moisture is one of the airplanes’ worst enemies in that it
deteriorates the weatherproofing and the fabric, distorts and otherwise
injures the wooden parts of the machines and worst of all, rusts the
metal parts, the first consideration for proper storage facilities
should be the absence of moisture. Next, extreme heat and cold are a
menace to airplanes. The temperature of the air surrounding them while
in storage should be regulated as much as possible. Under shelter,
especially when the machine is to be out of active service for 48
hr. or more, the entire machine should be raised off the ground a
few inches so that the wheels are free and the flexible connections
released. This is done by the points where the undercarriage struts
meet the skids. Furthermore, the wings might well be supported and
the weight thus taken off the landing wires, and hinge connections
by placing padded trestles underneath the wing skids. Care should be
exercised that dirt, grease, water, etc., does not accumulate in any
part of the airplane.
Furthermore, all water should be drained from the radiator and gasoline
from the gasoline tank. The propeller should be placed in a vertical
position and covered with a weatherproof cloth. The engine cockpit and
instruments should all be covered and the magneto should be enclosed in
a thick layer of felt or cotton waste. If any fluid is apt to freeze,
and oil will freeze in temperatures low enough, it should be carefully
drained.
When spare parts such as wings, struts, fuselages, etc., are stored,
the same general precautions outlined above should be observed. Spare
planes particularly should be placed in such a manner that their weight
is evenly supported. Never should planes of any kind be laid flat on
the ground. They should always stand edgewise, with the leading edge
down, supported several inches off the ground on blocks or boards
evenly spaced. One plane must not be allowed to lean against another.
In fact, the best way is to suspend planes by means of canvas slings
hung from overhead. Within the loop of the slings there must be a
batten about 2½ in. wide.
All parts of an airplane subject to attack by rust should be kept well
coated with grease or oil. Periodically the entire machine should be
wiped by means of clean, dry cheese cloth or selected cotton waste.
Engines which are in stored planes or which have been set aside for
future use should be turned over by hand daily.
It will sometimes be impossible for airplane sheds or hangars to be
brought up to the front on service, hence, airplanes must be prepared
to remain in the open. When this is the case they should be placed
to the leeward of the highest hedge available, a clump of trees, a
building, a bank, a knoll, or hill, etc. They should be sunk as low
as possible by digging a trench for the wheels and undercarriage.
The nose of the plane should, of course, first be run into the wind,
and then the wings and the tail pegged down with ropes, particularly
if there is any chance of a wind starting up. The engine, propeller,
instruments, and cockpit should be covered over with a waterproof cloth
and great care taken to protect the propeller from the sun, for it will
surely warp if not cared for properly. At night in cold or wet weather
the magneto should be packed round with waste and water in the radiator
drained. While machines are stored in the open, the necessity of wiping
them to keep them moisture and dirt free is all the more urgent and
should be pursued with doubled energy.
CHAPTER XI
INSPECTION OF AIRPLANES
Mechanics in charge of airplanes, who are primarily responsible for
their safety while in their care, should constantly think of new
methods for insuring greater safety and reliability. They should
invariably bring any fresh points they think of to the attention
of their Flight Commander, in order that the rest of the Corps may
benefit by them. They should always try to find out the _cause_ of
anything wrong, and inform the officer in charge of the machine of
their opinion. They should bear in mind any particular incidents which
may have happened to their machine while under their charge during
each flight, and be on the lookout for signs of stresses that may have
occurred to the machine in consequence of these incidents. For example,
a steep spiral may cause side strains on the engine bearers; a flight
in bad weather may cause bending stresses on the longitudinal members
of the body, besides stretching the landing and flying wires. No part
of a machine can be safely overlooked, and good mechanics will always
be seeking for the possible cause of accidents and bringing them to the
notice of the officer in charge of the machines.
During all inspections the following matters of detail deserve
particular attention:
Look out for dirt, dust, rust, mud, oil on fabric. Cleanliness is the
very first consideration.
Give the control cables particular attention. These should not be too
tight, otherwise they will rub stiffly in the guides. The hand should
be passed over them to detect kinks and broken strands. They should be
especially well examined where they run over pulley. Don’t forget the
aileron balance wire on the top plane.
See that all wires are well greased and oiled, and that they are all
in the same tension. When examining wires, be sure to have machine
on level ground as otherwise it may get twisted, throwing some wires
into undue tension and slackening others. The best way, if time is
available, is to jack the airplane up into “flying position.” If a
slack wire is found, do not jump to the conclusion that it must be
tensioned. Perhaps its opposite wire is too tight, in which case it
should be slackened.
Carefully examine all wires and their connections near the propeller,
and be sure that they are snaked around with safety wire, so that the
latter may keep them out of the way of the propeller if they come
adrift.
Carefully examine all surfaces, including the controlling surfaces,
to see whether any distortions have occurred. If distortions can be
corrected by adjustment of wires, well and good, but if not, matter
should be reported.
Verify the angles of incidence, the dihedral angle, the stagger,
and the overall measurements as often as possible (at least once a
week) and correct as outlined in notes on assembly and adjustment of
airplanes.
Constantly examine the alignment and fittings of the undercarriage, the
condition of tires, shock absorbers and the skids. Verify the rigging
position of the ailerons and elevators.
Constantly inspect the locking arrangements of the turnbuckles, bolts,
etc.
Learn to become an expert at vetting, which means the ability to judge
the alignment of the airplane and its parts by eye. Whenever you have
the opportunity practice sighting one strut against another to see that
they are parallel. Standing in front of the machine, which in such a
case should be on level ground, sight the center section plane against
the tail plane and see that the latter is in line. Sight the leading
edge against the main spars, the rear spars, and the trailing edges,
taking into consideration the “washin” and “washout.” You will be able
to see the shadow of the spars through the fabric. By practising this
sort of thing you will, after a time, become quite expert, and will be
able to diagnose by eye faults in efficiency, stability and control.
The following order should be observed in the daily and weekly
inspections:
=Daily Inspection.=—All struts and their sockets, longerons, skids,
etc.
All outside wires and their attachments.
All control levers or wheels, control wires and cable and their
attachments.
All splices for any signs of their drawing.
Lift and landing gear cables or wires for any signs of stretching.
All fabrics, whether on wings or other parts of the machine, for
holes, cuts, weak or badly doped places, or signs of being soaked with
gasoline, and to see if properly fastened to wings, etc.
All outside turnbuckles, to see that they have sufficient threads
engaged, and that they are properly locked.
Axles, wheels, shock absorbers, and tires, pumping the latter up to the
correct pressure.
The seats, both for passenger and pilot, seeing that they are fastened
correctly.
Safety belts and their fastenings.
This examination should be carried out systematically in the following
order:
(_a_) Lower wings, landing gear complete, tail planes with all wires
attached to these tail skids and all attachments and rudder.
(_b_) Nacelle or fuselage, bolts of lower plane, all control levers and
wires.
(_c_) Top wings, wing flaps or ailerons and wires.
_Inspection after Each Flight._—The landing gear, tail skid and
attachments and lift and drag wires for tautness.
The wheels, after a rough landing, for bent spokes, uncovering them if
necessary.
After flying is finished for the day, wipe all oil off the planes as
far as possible with a cloth or cotton waste.
_Weekly Inspection._—Check over all dimensions, span, chord, gap,
stagger of wings, angles of incidence or set angle of wings and tail,
dihedral angle, alignment of fuselage, rudder, elevators, and the
general truth of the machine.
Examine the points of crossing of all wires to see that there are no
signs of wear, and that each wire is properly bound with insulating
tape to prevent rubbing.
Examine all places where wires cross the strut to see if the plates
require renewal.
Examine any control wires which are bound together, and see that they
are correct. (Insulating tape should be used for this in preference to
wires which are bound to slip and cause slack.)
Examine the wheels for bent or loose spokes, uncovering if necessary.
Examine all nuts and bolts of cotter-pin applications, lock washers,
etc.
The following directions for inspection are given to the U. S.
Inspectors of Airplanes:
_Inspection of Cables._
Are there any kinks in the cable?
Are loops properly made?
Are thimbles used in eyes?
Are ends wrapped properly (when wrapped splice is used, wrap must be at
least fifteen times the diameter of wire).
No splicing of the cable itself is permitted.
Has acid struck cable during soldering?
Are any of the strands broken?
Are unwrapped ends stream-lined and show the result of skilled
workmanship?
_For Roebling Hard Wire._
Are there any file cuts or flaws to weaken it?
Is loop well made?
Is ferrule put on correctly?
Are there any sharp bends or kinks?
Are wires too loose or tight in machine?
_Fittings._
Is workmanship good?
Is material good?
Are holes drilled correctly to develop proper strength?
Are there any deep file cuts or flaws to weaken it?
Is rivet or fastening wire put in properly?
Are thimbles of large enough diameter?
_Turnbuckles._
Any file cuts, tool marks, or flaws in shank or barrel?
Are there too many threads exposed?
Is turnbuckle of right strength and size to develop full strength of
wire?
Are shanks bent?
Are threads on shank or in barrel well made?
Is barrel cracked?
Is turnbuckle properly wired?
_Inspection of Linen._
All linen used in airplane construction should be of the following
specifications:
Free from all knots or kinks.
Without sizing or filling.
As near white as possible.
Weight, between 3.5 and 4.5 oz. per square yard.
Strength as per Government Specifications.
_Inspection of Wood._
All wood should be inspected before varnish is applied.
Is grain satisfactory?
Are there any sap or worm holes?
Are there any knots that look as if they would weaken the member?
Any brashiness?
Any holes drilled for bolts or screws that would weaken the member?
Any splits or checks?
Are laminations glued properly?
Are there any plugged holes?
Any signs of dry rot?
_Inspection of Metal Fittings._
When fittings are copper plated and japanned the inspection should take
place after the copper plating.
Have fittings been bent in assembling?
Does fitting show any defects that lessen its strength?
Are holes drilled properly. Do fittings fit?
Sheet aluminum should be inspected for defects such as cracks, bad
dents, etc. Where openings occur in sheet aluminum the corners should
be rounded, allowing a good-sized radius.
_Directions for Work._
Before you start work on rigging you are advised as follows:
1. Do not hurry about the work. No rush jobs can be done in airplane
rigging.
2. You are cautioned against leaving tools of any kind in any part of
the airplane.
3. The bolts and their threads must not be burred in any way; for this
reason, the use of pliers or pipe wrenches on bolts is very bad form.
4. Start all turnbuckles from both ends every time they are connected
up.
5. Full threads must be had in every case to develop the full strength
of a bolt and nut, with turnbuckles at least turn on for a distance
equal to three times the thickness of the shank.
6. Lock with safety wires all turnbuckles and pins, and cotter-pin
every nut.
7. Watch for kinking of wires and their rubbing around controls and
wherever they may vibrate against one another.
8. All bolts and pins must have an easy tapping fit only; do not pound
them into position.
Transcriber’s Notes
pg 22 Changed: funished with dual control
to: furnished with dual control
pg 83 Changed: rather than flying off in a straight ine
to: rather than flying off in a straight line
pg 86 Changed: to get out of an immanent pancake
to: to get out of an imminent pancake
*** END OF THE PROJECT GUTENBERG EBOOK LEARNING TO FLY IN THE U.S. ARMY ***
Updated editions will replace the previous one—the old editions will
be renamed.
Creating the works from print editions not protected by U.S. copyright
law means that no one owns a United States copyright in these works,
so the Foundation (and you!) can copy and distribute it in the United
States without permission and without paying copyright
royalties. Special rules, set forth in the General Terms of Use part
of this license, apply to copying and distributing Project
Gutenberg™ electronic works to protect the PROJECT GUTENBERG™
concept and trademark. Project Gutenberg is a registered trademark,
and may not be used if you charge for an eBook, except by following
the terms of the trademark license, including paying royalties for use
of the Project Gutenberg trademark. If you do not charge anything for
copies of this eBook, complying with the trademark license is very
easy. You may use this eBook for nearly any purpose such as creation
of derivative works, reports, performances and research. Project
Gutenberg eBooks may be modified and printed and given away—you may
do practically ANYTHING in the United States with eBooks not protected
by U.S. copyright law. Redistribution is subject to the trademark
license, especially commercial redistribution.
START: FULL LICENSE
THE FULL PROJECT GUTENBERG LICENSE
PLEASE READ THIS BEFORE YOU DISTRIBUTE OR USE THIS WORK
To protect the Project Gutenberg™ mission of promoting the free
distribution of electronic works, by using or distributing this work
(or any other work associated in any way with the phrase “Project
Gutenberg”), you agree to comply with all the terms of the Full
Project Gutenberg™ License available with this file or online at
www.gutenberg.org/license.
Section 1. General Terms of Use and Redistributing Project Gutenberg™
electronic works
1.A. By reading or using any part of this Project Gutenberg™
electronic work, you indicate that you have read, understand, agree to
and accept all the terms of this license and intellectual property
(trademark/copyright) agreement. If you do not agree to abide by all
the terms of this agreement, you must cease using and return or
destroy all copies of Project Gutenberg™ electronic works in your
possession. If you paid a fee for obtaining a copy of or access to a
Project Gutenberg™ electronic work and you do not agree to be bound
by the terms of this agreement, you may obtain a refund from the person
or entity to whom you paid the fee as set forth in paragraph 1.E.8.
1.B. “Project Gutenberg” is a registered trademark. It may only be
used on or associated in any way with an electronic work by people who
agree to be bound by the terms of this agreement. There are a few
things that you can do with most Project Gutenberg™ electronic works
even without complying with the full terms of this agreement. See
paragraph 1.C below. There are a lot of things you can do with Project
Gutenberg™ electronic works if you follow the terms of this
agreement and help preserve free future access to Project Gutenberg™
electronic works. See paragraph 1.E below.
1.C. The Project Gutenberg Literary Archive Foundation (“the
Foundation” or PGLAF), owns a compilation copyright in the collection
of Project Gutenberg™ electronic works. Nearly all the individual
works in the collection are in the public domain in the United
States. If an individual work is unprotected by copyright law in the
United States and you are located in the United States, we do not
claim a right to prevent you from copying, distributing, performing,
displaying or creating derivative works based on the work as long as
all references to Project Gutenberg are removed. Of course, we hope
that you will support the Project Gutenberg™ mission of promoting
free access to electronic works by freely sharing Project Gutenberg™
works in compliance with the terms of this agreement for keeping the
Project Gutenberg™ name associated with the work. You can easily
comply with the terms of this agreement by keeping this work in the
same format with its attached full Project Gutenberg™ License when
you share it without charge with others.
1.D. The copyright laws of the place where you are located also govern
what you can do with this work. Copyright laws in most countries are
in a constant state of change. If you are outside the United States,
check the laws of your country in addition to the terms of this
agreement before downloading, copying, displaying, performing,
distributing or creating derivative works based on this work or any
other Project Gutenberg™ work. The Foundation makes no
representations concerning the copyright status of any work in any
country other than the United States.
1.E. Unless you have removed all references to Project Gutenberg:
1.E.1. The following sentence, with active links to, or other
immediate access to, the full Project Gutenberg™ License must appear
prominently whenever any copy of a Project Gutenberg™ work (any work
on which the phrase “Project Gutenberg” appears, or with which the
phrase “Project Gutenberg” is associated) is accessed, displayed,
performed, viewed, copied or distributed:
This eBook is for the use of anyone anywhere in the United States and most
other parts of the world at no cost and with almost no restrictions
whatsoever. You may copy it, give it away or re-use it under the terms
of the Project Gutenberg License included with this eBook or online
at www.gutenberg.org. If you
are not located in the United States, you will have to check the laws
of the country where you are located before using this eBook.
1.E.2. If an individual Project Gutenberg™ electronic work is
derived from texts not protected by U.S. copyright law (does not
contain a notice indicating that it is posted with permission of the
copyright holder), the work can be copied and distributed to anyone in
the United States without paying any fees or charges. If you are
redistributing or providing access to a work with the phrase “Project
Gutenberg” associated with or appearing on the work, you must comply
either with the requirements of paragraphs 1.E.1 through 1.E.7 or
obtain permission for the use of the work and the Project Gutenberg™
trademark as set forth in paragraphs 1.E.8 or 1.E.9.
1.E.3. If an individual Project Gutenberg™ electronic work is posted
with the permission of the copyright holder, your use and distribution
must comply with both paragraphs 1.E.1 through 1.E.7 and any
additional terms imposed by the copyright holder. Additional terms
will be linked to the Project Gutenberg™ License for all works
posted with the permission of the copyright holder found at the
beginning of this work.
1.E.4. Do not unlink or detach or remove the full Project Gutenberg™
License terms from this work, or any files containing a part of this
work or any other work associated with Project Gutenberg™.
1.E.5. Do not copy, display, perform, distribute or redistribute this
electronic work, or any part of this electronic work, without
prominently displaying the sentence set forth in paragraph 1.E.1 with
active links or immediate access to the full terms of the Project
Gutenberg™ License.
1.E.6. You may convert to and distribute this work in any binary,
compressed, marked up, nonproprietary or proprietary form, including
any word processing or hypertext form. However, if you provide access
to or distribute copies of a Project Gutenberg™ work in a format
other than “Plain Vanilla ASCII” or other format used in the official
version posted on the official Project Gutenberg™ website
(www.gutenberg.org), you must, at no additional cost, fee or expense
to the user, provide a copy, a means of exporting a copy, or a means
of obtaining a copy upon request, of the work in its original “Plain
Vanilla ASCII” or other form. Any alternate format must include the
full Project Gutenberg™ License as specified in paragraph 1.E.1.
1.E.7. Do not charge a fee for access to, viewing, displaying,
performing, copying or distributing any Project Gutenberg™ works
unless you comply with paragraph 1.E.8 or 1.E.9.
1.E.8. You may charge a reasonable fee for copies of or providing
access to or distributing Project Gutenberg™ electronic works
provided that:
• You pay a royalty fee of 20% of the gross profits you derive from
the use of Project Gutenberg™ works calculated using the method
you already use to calculate your applicable taxes. The fee is owed
to the owner of the Project Gutenberg™ trademark, but he has
agreed to donate royalties under this paragraph to the Project
Gutenberg Literary Archive Foundation. Royalty payments must be paid
within 60 days following each date on which you prepare (or are
legally required to prepare) your periodic tax returns. Royalty
payments should be clearly marked as such and sent to the Project
Gutenberg Literary Archive Foundation at the address specified in
Section 4, “Information about donations to the Project Gutenberg
Literary Archive Foundation.”
• You provide a full refund of any money paid by a user who notifies
you in writing (or by e-mail) within 30 days of receipt that s/he
does not agree to the terms of the full Project Gutenberg™
License. You must require such a user to return or destroy all
copies of the works possessed in a physical medium and discontinue
all use of and all access to other copies of Project Gutenberg™
works.
• You provide, in accordance with paragraph 1.F.3, a full refund of
any money paid for a work or a replacement copy, if a defect in the
electronic work is discovered and reported to you within 90 days of
receipt of the work.
• You comply with all other terms of this agreement for free
distribution of Project Gutenberg™ works.
1.E.9. If you wish to charge a fee or distribute a Project
Gutenberg™ electronic work or group of works on different terms than
are set forth in this agreement, you must obtain permission in writing
from the Project Gutenberg Literary Archive Foundation, the manager of
the Project Gutenberg™ trademark. Contact the Foundation as set
forth in Section 3 below.
1.F.
1.F.1. Project Gutenberg volunteers and employees expend considerable
effort to identify, do copyright research on, transcribe and proofread
works not protected by U.S. copyright law in creating the Project
Gutenberg™ collection. Despite these efforts, Project Gutenberg™
electronic works, and the medium on which they may be stored, may
contain “Defects,” such as, but not limited to, incomplete, inaccurate
or corrupt data, transcription errors, a copyright or other
intellectual property infringement, a defective or damaged disk or
other medium, a computer virus, or computer codes that damage or
cannot be read by your equipment.
1.F.2. LIMITED WARRANTY, DISCLAIMER OF DAMAGES - Except for the “Right
of Replacement or Refund” described in paragraph 1.F.3, the Project
Gutenberg Literary Archive Foundation, the owner of the Project
Gutenberg™ trademark, and any other party distributing a Project
Gutenberg™ electronic work under this agreement, disclaim all
liability to you for damages, costs and expenses, including legal
fees. YOU AGREE THAT YOU HAVE NO REMEDIES FOR NEGLIGENCE, STRICT
LIABILITY, BREACH OF WARRANTY OR BREACH OF CONTRACT EXCEPT THOSE
PROVIDED IN PARAGRAPH 1.F.3. YOU AGREE THAT THE FOUNDATION, THE
TRADEMARK OWNER, AND ANY DISTRIBUTOR UNDER THIS AGREEMENT WILL NOT BE
LIABLE TO YOU FOR ACTUAL, DIRECT, INDIRECT, CONSEQUENTIAL, PUNITIVE OR
INCIDENTAL DAMAGES EVEN IF YOU GIVE NOTICE OF THE POSSIBILITY OF SUCH
DAMAGE.
1.F.3. LIMITED RIGHT OF REPLACEMENT OR REFUND - If you discover a
defect in this electronic work within 90 days of receiving it, you can
receive a refund of the money (if any) you paid for it by sending a
written explanation to the person you received the work from. If you
received the work on a physical medium, you must return the medium
with your written explanation. The person or entity that provided you
with the defective work may elect to provide a replacement copy in
lieu of a refund. If you received the work electronically, the person
or entity providing it to you may choose to give you a second
opportunity to receive the work electronically in lieu of a refund. If
the second copy is also defective, you may demand a refund in writing
without further opportunities to fix the problem.
1.F.4. Except for the limited right of replacement or refund set forth
in paragraph 1.F.3, this work is provided to you ‘AS-IS’, WITH NO
OTHER WARRANTIES OF ANY KIND, EXPRESS OR IMPLIED, INCLUDING BUT NOT
LIMITED TO WARRANTIES OF MERCHANTABILITY OR FITNESS FOR ANY PURPOSE.
1.F.5. Some states do not allow disclaimers of certain implied
warranties or the exclusion or limitation of certain types of
damages. If any disclaimer or limitation set forth in this agreement
violates the law of the state applicable to this agreement, the
agreement shall be interpreted to make the maximum disclaimer or
limitation permitted by the applicable state law. The invalidity or
unenforceability of any provision of this agreement shall not void the
remaining provisions.
1.F.6. INDEMNITY - You agree to indemnify and hold the Foundation, the
trademark owner, any agent or employee of the Foundation, anyone
providing copies of Project Gutenberg™ electronic works in
accordance with this agreement, and any volunteers associated with the
production, promotion and distribution of Project Gutenberg™
electronic works, harmless from all liability, costs and expenses,
including legal fees, that arise directly or indirectly from any of
the following which you do or cause to occur: (a) distribution of this
or any Project Gutenberg™ work, (b) alteration, modification, or
additions or deletions to any Project Gutenberg™ work, and (c) any
Defect you cause.
Section 2. Information about the Mission of Project Gutenberg™
Project Gutenberg™ is synonymous with the free distribution of
electronic works in formats readable by the widest variety of
computers including obsolete, old, middle-aged and new computers. It
exists because of the efforts of hundreds of volunteers and donations
from people in all walks of life.
Volunteers and financial support to provide volunteers with the
assistance they need are critical to reaching Project Gutenberg™’s
goals and ensuring that the Project Gutenberg™ collection will
remain freely available for generations to come. In 2001, the Project
Gutenberg Literary Archive Foundation was created to provide a secure
and permanent future for Project Gutenberg™ and future
generations. To learn more about the Project Gutenberg Literary
Archive Foundation and how your efforts and donations can help, see
Sections 3 and 4 and the Foundation information page at www.gutenberg.org.
Section 3. Information about the Project Gutenberg Literary Archive Foundation
The Project Gutenberg Literary Archive Foundation is a non-profit
501(c)(3) educational corporation organized under the laws of the
state of Mississippi and granted tax exempt status by the Internal
Revenue Service. The Foundation’s EIN or federal tax identification
number is 64-6221541. Contributions to the Project Gutenberg Literary
Archive Foundation are tax deductible to the full extent permitted by
U.S. federal laws and your state’s laws.
The Foundation’s business office is located at 809 North 1500 West,
Salt Lake City, UT 84116, (801) 596-1887. Email contact links and up
to date contact information can be found at the Foundation’s website
and official page at www.gutenberg.org/contact
Section 4. Information about Donations to the Project Gutenberg
Literary Archive Foundation
Project Gutenberg™ depends upon and cannot survive without widespread
public support and donations to carry out its mission of
increasing the number of public domain and licensed works that can be
freely distributed in machine-readable form accessible by the widest
array of equipment including outdated equipment. Many small donations
($1 to $5,000) are particularly important to maintaining tax exempt
status with the IRS.
The Foundation is committed to complying with the laws regulating
charities and charitable donations in all 50 states of the United
States. Compliance requirements are not uniform and it takes a
considerable effort, much paperwork and many fees to meet and keep up
with these requirements. We do not solicit donations in locations
where we have not received written confirmation of compliance. To SEND
DONATIONS or determine the status of compliance for any particular state
visit www.gutenberg.org/donate.
While we cannot and do not solicit contributions from states where we
have not met the solicitation requirements, we know of no prohibition
against accepting unsolicited donations from donors in such states who
approach us with offers to donate.
International donations are gratefully accepted, but we cannot make
any statements concerning tax treatment of donations received from
outside the United States. U.S. laws alone swamp our small staff.
Please check the Project Gutenberg web pages for current donation
methods and addresses. Donations are accepted in a number of other
ways including checks, online payments and credit card donations. To
donate, please visit: www.gutenberg.org/donate.
Section 5. General Information About Project Gutenberg™ electronic works
Professor Michael S. Hart was the originator of the Project
Gutenberg™ concept of a library of electronic works that could be
freely shared with anyone. For forty years, he produced and
distributed Project Gutenberg™ eBooks with only a loose network of
volunteer support.
Project Gutenberg™ eBooks are often created from several printed
editions, all of which are confirmed as not protected by copyright in
the U.S. unless a copyright notice is included. Thus, we do not
necessarily keep eBooks in compliance with any particular paper
edition.
Most people start at our website which has the main PG search
facility: www.gutenberg.org.
This website includes information about Project Gutenberg™,
including how to make donations to the Project Gutenberg Literary
Archive Foundation, how to help produce our new eBooks, and how to
subscribe to our email newsletter to hear about new eBooks.
