Technical orders no. 26

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AIR SERVICE INFORMATION CIRCULAR
VOLUME IV.
AVIATION AND AEROSTATION
BY DIRECTION OF CHIEF OF AIR SERVICE
DAYTON, OHIO, JUNE, 1922
TECHNICAL ORDERS
No.26
ENGINEERING DIVISION
AIR SERVICE
CONFIDENTIAL
NUMBER 351
CONFIDENTIAL.
The information contained herein is confidential and must not be
published, either in whole or in part, ·without express permission· of the
•
Chief of Air Service.
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AIR SERVICE
TECHNICAL ORDERS
No. 26
, CONTENTS FOR JUNE, 1922
NEW DESIGN
Page
Airplanes -------- --- --- ----- --- ------- ·······- -·····-·--· ··- -··---------- -··------- ----_----·--'------- ·---- --- ---- 4
Balloons and Airships ----- ---------- -··--·-· --- --- ---~-- -- ------ ------ -- ---- -------· ·-· ____ ____________ 7
Engines, Including Article on Rausie "E-6" Aviation Engine ____ ______ ________ 10
Armament ·---- --- ·· -- -- -·--- ---- ---------- -·------- ------ ---- -- ------ ---·----------- ----------------- -· ------ ---- 14
Equipment --- -- --- --- ---------- -·--------------- -- ---· ----- ---·--------------·---·------····--···· ---- ---- ----- - 16
EXPERIMENTATION
Resume of Engineering Division Serial Reports --- -----···-- ---------- --- -- ------- --- 18
FOREIGN DEVELOPMENT
Aviation Material in France ___ ____ _______ -- --- --- ------ -· ------ -- ------------- -- --- ·----------- --· 27
French Military Airplanes (late types) __ ---- ------- ------------ ---·-----·· ------------- -- -- 27
NEW BOOKS AND DOCUMENTS
Latest Documents on Aeronautics- --- -· -- ·-·--·------ --- --------------- ----·· ·- __________ __ ____ 35
R~cent Accessions to Engineering Division Library--- ----- -- ·----·- -···· ·-···--- --- 50
NEW DESIGN
AIRPLANES
TYPE I-SINGLE-SEATER DAY PURSUIT
Loening PW-2B (Packard "lA-1237" 300 h.p. Engine).
The results of the performaneie trials including special cooling tests, recently
completed, indicate that this airplane will be unsatisfactory for Type I requirements.
A detailed report of the test is being prepared.
Fokker PW-5 (Wright "H" 300 h.p. Engine)-Pormerly "V-40".
The static tests of the Fokker "V-40" have been completed and the structural
changes to be incorporated in the production models have been forwarded.
The production model, designated the "PW-5", ten of which have been ordered
from Anthony H. G. Fokker of Holland, will be similar to the model "V-40" except that
a new plywood wing, identical to the redesigned wing recently static tested, a steerable
tailskid, and a full floating landing gear axle will be installed.
Another contract has been placed for two metal wings for this airplane having
the same external characteristics as the new plywood wing. This wing will have a
metal structure, either of duralumin or steel or a combination of-both, with fabric cover­ing
except for the leading edge, from the front spar forward, which will be covered .
top and bottom with duralumin. The weight of the metal wing including ailerons will
be approximately 520 pounds.
Boeing MB-3A (Wright "H-3" 300 h.p. Engine).
The first airplane, completed in June by the Boeing Company on this contract
for two hundred, was damaged while taxying over bad terrain after landing from its
initial flight test at the company's plant and, consequently, no performance has been
obtained.
TYPE II-SINGLE-SEATER NIGHT PURSUIT
No experimentation is contemplated on this type·at present
4 '
New Design-Airplanes
TYPE III-SINGLE-SEATER PURSUIT (AIR-COOLED ENGINE)
Loening PA-1 (Wright "Radial" 350 h.p. Engine).
Flight t ests have been delayed pending the arrival of the engine for this airplane.
TYPE IV-SINGLE-SEATER ARMORED PURSUIT
Engineering Division PG-1 (Wright "K-2" 300 h.p. Engine).
A Wright "H-2" engine has been installed in this airplane for flight test.
TYPE V-TWO-SEATER PURSUIT
Engineering Division TP-1 (Liberty "12" Supercharged Engine).
Satisfactory progress is being made in the construction of this model.
TYPE VI-ARMORED GROUND ATTACK
Boeing GA-2 (Model "W-lA" 700 h.p. Engine).
Preliminary flight tests are in progress.
TYPES VII, VIII, AND IX.
No experimentation is in progress on these types at present.
TYPE X-CORPS OBSERVATION
Engineering Division C0-1 (Liberty "12" Supercharged Engine). ,
A new landing gear has been installed and tested, and flight tests of the airplane
are being continued.
A contract for three production airplanes has been awarded to the Gallaudet Air­craft
Corporation of New York.
Engineering Division C0-2 (Liberty "12" Engine).
Static tests are in progress on the first airplane of this design.
Fokker C0-4 (Liberty "12" Engine).
The performance tests of the first airplane have been completed and the changes
to be incorporated in the two remaining airplanes on this contract are being prepared.
5
New Design-Airplanes
TYPE XI-DAY BOMBARDMENT
Gallaudet DB-1 (Model "W-lA" 700 h.p. Engine).
Work on the redesigned airplane of this type is proceeding satisfactorily.
TYPE XII-NIGHT BOMBARDMENT-SHORT DISTANCE
Curtiss NBS-1 (Two Liberty "12" Engines).
Two airplanes have been delivered to Mitchell Field by the Curtiss Aeroplane
and Motor Corporation where flight tests are in progress.
L-W-F NBS-1 (Two Liberty "12" Engines).
The first of the thirty-five airplanes being built by the L. W. F. Company was
delivered to the Aeromarine Plane & Motor Company for a production model. The re­maining
thirty-four· airplanes, three of which have been completed, are to be prepared
for over-seas shipment.
TYPE XIII-NIGHT BOMBARDMENT~LONG DIBTANCE
NHL-1 (Six Liberty "12" Engines).
The construction of this airplane is practically completed.
TYPE XIV-TRAINING (AIR-COOLED ENGINF;)
Huff-Daland TA-2 Airplanes.
Both models of this airplane, one equipped with the Curtiss "OX-5" engine and
the other with the Lawrance "R-1" engine, are awaiting performance trials.
TYPE XV-TRAINING (WATER-COOLED ENGINE)
Cox-Klemin TW-2 (Wright "I" 150 h.p. Engine).
Static tests of the first airplane are in progress.
SPECIAL TYPE.
Dayton Wright PS-1 (Lawrance "J-1" 220 h.p. Engine).
The delivery date of the first airplane of this type has been extended to August.
MISCELLANEOUS PROJECTS.
Fokker Transport "F-IV" (Liberty "12" Engine).
Several changes including the installation of a booster radiator and an air scoop
for cooling pilot's cockpit have been made and performance tests continued.
6
New Design
BALLOONS AND AIRSHIPS
U. S. M. B. Airship (Two Lawrance 60 h.p. Engines).
This airship has been fully described in Technical Orders No. 23, page 14, and
delivery of the ship is expected shortly after August 1, 1923.
A thorough series of tests has been outlined for determining the operation of this
craft under the various service conditions.
Navy Towing Ship.
The Navy Towing Ship is an airship of approximately 45,000 cu.ft. capacity,
equipped with one Lawrance 60 h.p. engine and designed by the Navy for the same pur­pose
as that for which the U. S. M. B. was designed by the Army; i.e., a motorized ob­servation
balloon to supplant the present type of captive balloon.
This ship is now due to be delivered at Wilbur Wright Field, and as soon as it is
erected, tests will be carried out similar to those contemplated for the U. S. M. B.
The Navy has requested permission to have an observer present at these tests in­asmuch
as the . first ship of this type was destroyed by fire at Rockaway Air Station
before any test could be made.
High Altitude Observation Balloon (Helium-50,000 cu.ft. Capacity).
An early delivery of this balloon is anticipated and preparations have been made
for immediate test of its lift and stability under service condjtions.
Spherical Balloon, High Altitude (80,000 r.u.ft. Capacity).
,
The design of this balloon has been completed and the contract let to · Goodyear
Tire & Rubber Co. for delivery on or about S_eptember 1st.
After exhaustive tests of materials it was finally determined to construct the en­velope
of rubberized silk fabric with an outside coating of aluminum. Tests of var­nished
materials proved that they would be unsatisfactory under the conditions of ex­treme
cold that would be encountered in experiments of -the nature for which this balloon
is intended.
7
New Design-Balloons and Airships
Triangulation Balloons.
Tests and experiments of the Triangulation Balloon mentioned in Technical
Orders No. 23, page 18, have been conducted and have given very favorable results. The
tail cups have been replaced by fixed surfaces which have resulted in greater stability.
In triangulation work it was found that the apex of the three wires, above which the
balloon was flown, remained steady to such an extent that accurate results in triangu­lation
work can be obtained.
Additional tests are under way for the purpose of lighting the balloon so as to
permit its serving as a marker for landing fields.
Portable Mooring Mast ( Gun Mount Type).
A contract has been let for the construction of one mast for delivery about October
1, 1922, at which time a test will be conducted in conjunction with one of the smaller air­ships.
Helium Gas Cell.
The placing of a contract for this cell has been held up for the pi,esent due to the
excessive cost of same and the fact that experiments with substitutes for goldbeater
skin have progressed to such a point that it is believed the test of the cell itself and of
the new material can be carried on at the same time.
TRANSPORTATION EQUIPMENT
Highly Mobile Balloon Winch.
This winch has been delivered by the Freeman Motor Company, and in the road
test en route from Cleveland, Ohio, to McCook Field and in such tests as have been· con­ducted
to date, it has performed very satisfactorily.
Several tests covering the operation of this winch both with and without balloon
attached, are to be conducted in the immediate future.
Track-Laying Adapter for Balloon Winch.
The construction of this adapter is being carried on at this Station and is 50%
completed. It will be tested in conjunction with the Highly Mobile Balloon Winch.
Balloon Tender.
The design of this tender has been completed and contract let to the Steel Prod­ucts
Co., Springfield, Ohio, for delivery about November ~' 1922.
The chassis of the tender will incorporate the essential features of the Highly
Mobile Winch that is described in Technical Orders No. 24, page 11.
8
New Design-Balloons and Airships
Compressor for Light-Weight Truck.
The contract for this truck has been placed with the above mentioned company
and delivery will be made about November 1, 1922.
The chassis of the truck is similar to that of the Highly Mobile Winch and the
equipment of the truck is described in Technical Orders No. 24.
Electrolytic Cell.
The delivery of six units has been made and tests have been started to determine
their efficiency at the plant of the Dayton Oxygen & Hydrogen Company where facilities
are at hand for determining the conduct of these cells under all conditions of load.
7m Continuous Gas Plant.
This plant as described in Technical Orders No. 24 has been delivered and set up
at Wilbur Wright Field where tests will be conducted as soon as the aircraft and the
compressor machinery are available.
Silicol Hydrogen Generator-Railway Unit.
This unit has been delivered at Langley Field and a series of tests has been out­lined
that will be conducted simultaneously with the tests of the helium-filled airship
at that Station.
Blower Unit for U. S. M. B.
This project was initiated by the Lighter-than-Air Section and the design and
construction of the blower carried on by the Propeller Branch, this Station.
At the present time a blower which is apparently satisfactory has been evolved,
and further tests will be made at an early date.
Helium Experiments.
A series of exhaustive tests is now under way at Langley Field, under the super­vision
of Engineering Division Representative, for the determination of the various
questions entering into the operation of airships when inflated with helium.
At the same time, tests are being made of inflation apparatus, inflation mani­folds
and gas valves which have been designed by this Section.
9
New Design
ENGINES
AIR-COOLED TYPES
Lawrance "J-1" 220 h.p., 9-Cylinder.
The design of a cylinder known as. the type "K" for this engine is practically
completed, and the construction of parts for one cylinder for testing purposes has been
started in the shop. The cylinder consists of an aluminum alloy head screwed to
a steel barrel and is very similar in construction to the type "J" cylinder designed for the
Wright radial engine, except that it is a smaller size and has inclosed valve gear. The
head carries two valves of the tulip type and provides a hemispherical combustion
chamber.
Preliminary tests have been run on a heating device designed for preventing the
formation of frost on the intake passages on this engine. The results of these tests in­dicate
that this device will keep the temperature within the manifold equal to that of the
outside air at all engine speeds, and prevent the formation of frost down to air tem­peratures
of 32° F.
Performance tests of the engine, with the original carburetor setting, have
been completed. However, different settings are to be tried out and upon the receipt of
the necessary chokes for the carburetor the tests will be continued.
Wright "Radial" 350 h.p., 9-Cylinder.
The contracts covering the construction of three of these engines have been ter­minated
and the engines are being prepared for shipment to this Division. The 50-hour
endurance test at the manufacturer's plant, provided for in the contract, has been can­celled
and will be conducted at this Division as soon as an engine is available.
A brief description of the engine follows:
Bore ------ -···----········-·····-···-----····--··-··---··---55/8"
Stroke ----- --·----· -·--- ------ -- ----- ---·· ·-·· ___________ 61J2"
Piston displaoement ---· ··-- -· -- ··-· -·-- ··-----·1453.5 cu.in.
Compression ratio ----- ------· ____ ___ __________ -_5.41 to 1
Rated output --------- --- -- --··-·-····-· ·--- ------···350 h.p. at 1650 r.p.m.
Actual output on test ___ ____ _______ ______ _____ 359.6 h.p. at 1670 r.p.m.
Weight-dry ···--· ···------·-"- ---···-· ·-- ___________ 859 lb.
WATER-COOLED TYPES
Almen "1-B" 375 h.p., IS-Cylinder.
Performance test of this engine has been delayed due to bearing trouble experi­enced
during the forming-up run on the dynamometer. This was caused by the failure
of the spacers in the wabble-plate bearings. The bearings have been repaired by the
manufacturers and the engine is being reassembled.
10
New Design-Engines
Model "W-IA" 700 h.p., IS-Cylinder.
The third 50-hour endurance test on this engine was successfully completed on
June 15th. Failures of minor parts only occurred during this test, and none were of suf.
ficient importance to make a forced stop necessary.
Rausie "E-6" 160 h.p., 6-Cylinder (Modified).
The Rausie ''E-6" aviation engine which ~has been under development for the past
two years, is a six-cylinder, vertical type, water-cooled engine manufactured by the
Steel Products Company, Springfield, Ohio. It has a neat appearance, is adapted to air­plane
installation, and with minor changes in design has been recommended for train­ing
purposes.
The first engine, a complej;e description of which is given in the standard engine
report in Air Service Information Circular No. 191 (Eng. Div. Serial No. 1430) was
tested by the Engineering Division in 1920 with recommendations for further develop­ment.
In the following year, a second eng;ne, incorporating these recommendations,
completed a fifty-hour endurance run with satisfactory results (Eng. Div. Serial No.
1760-A. S. I. C. in course of preparation). Since then, a number of modifications have
been made and tests of the modified engine have been completed recently.
The characteristic features of this engine are: (a) Steel machined cylinders
threaded at the upper end to screw into individual aluminum castings which comprise
the cylinder head, valve port, and water jackets, the lower end of which fits against
gaskets held in place by flange on the cylinder; (b) a valve gear of novel design elimin-ating
excessive side thrust on th·e valve stem and valve stem guides. ·
The principal changes which differentiate the modified from the original engine
are as follows.
WEIGHT-The dry weight of engine with propeller hub wai. increased from
534.4 to 550 lbs.
CRANKCASES-The lower half uses a box girder type web in which the lower
bearing caps are secured. The webs do not come up to the plane of the parting flange
thus facilitating the assembly of the upper and lower halves.
The separate oil pipe has been replaced by a "cast-in", steel oil pipe.
nozzles serve as dowel pins for bearings in the lower half of the crankcase.
bolts fastened in the usual manner in the lower crankcase are used.
The oil
Thru-
The rear end of the crankcase has been designed with the bolt circle like that
on the Liberty engine, to provide mounting for starter if desired.
CRANKSHAFT-The width and thickness of the crank cheeks and the bove of
the main journals are increased. The propeller hub taper has been changed to fit the
standard Wright Model "E" hub.
BEARINGS-The usual service type of bearings with bronze backs lined with
white metal held in place by dowel pins are fitted.
The thrust bearing is a Hess Bright single row ball, 8-ball bearing. A double row
40-ball SKF bearing was used in the original design.
11
New Design-Engines
CONNECTING RODS-A full £103:ting wrist pin is now used in connection with
Liberty type aluminum piston pin retainers. Shims have been eliminated at the lower
rod bearings.
VALVE GEAR-A locking device for the tappet bolts consisting of two springs
riveted to the plunger guide has been provided.
MAGNETO COUPLINGS-A flexible and adjustable coupling has been furnished
which gives an adjustment as low -as two degrees.
CARBURETION-Two Stromberg NA-S5 double Venturi carburetors with stan­dard
back-suction · altitude control have replaced the Miller carburetors formerly used.
Lunkenheimer primin·g cups have been installed in the intake manifold, one over
each intake valve.
COOLING SYSTEM-The water pump stuffing-box nuts have been notched to
permit use of spanner wrench. Two screws supported in the water pump body are used
to hold the stuffing-box nuts in place.
FUEL SYSTEM-An attachment for driving the gasoline pump through a ·worm
gear at crankshaft speed has been made on the oil and water pumps assembly. _
-
LUBRICATION-The oil pump screens have been made larger and of coarser
mesh. A spring-loaded, externally-adjustable pressure relief is located on the lower
right-hand side of the crankcase.
The performance of the modified engine as received. from the manufacturer with
a compression ratio of 5.63 :1 was unsatisfactory as it was impossible to run the engine
at full throttle and normal speed with either unblended aviation gasoline or mixed fuel
without serious detonation. The engine was then fitted with low compression pistons
having a compression ratio of 4.80 :1. A summary of the t est results are given in the
table.
Bore and stroke .. ..................... .. .. ....... .... .... .. ... ............. ... 5x6 (inches)
Total displacement ................... ...... ... . ... .. .. .... ........ ........... 706.86 cu.in.
Compression ratio ... ....... ... . .... · .. .. _ .. ............. .............. .4.80: 1
Normal speed ......... .......... ......... .... ...... . ..... .. .. ...... .... ........... 1650 r.p.m.
N:ormal brake horsepower at full throttle ..... .... _ ....... .. ... 162.6 at 1650 r .p.m
Normal brake mean effective pressure ............ .......... ...... 110.5 lb./ sq.in.
Fuel consumption at normal brake horsepower ......... .. 0.508 lb./ h.p.hr.
Oil consumption at normal brake horsepower .... ..... .... 0.0084 lb./h.p.hr.
Total weight dry with hub ... .. ................................... .... .. 550 lb.
Weight dry per normal brake horsepower .. .. .. .... ........ ~ .. 3.38 lb.
The power output of the engine with low comp11ession pistons was lower than
the original rated horsepower (175 b.h.p.). However, the engine ran smoothly at all
speeds on unblended fuel, the fuel consumption being normal and the oil consumption
remarkably low compared with other aviation engines. In its present stage of develop­ment,
it is hardly fair to compare this engine with either the Liberty "6" or the Curtiss
"C-6" engine for, with modifications in the cylinder design, the performance of the
Rausie engine could undoubtedly be improved.
12
New Design-Engines
Propeller End
Magneto End
RAUSIE "E-6" AVIATION ENGINE
13
New Design
ARMAMENT
BOMBING
Control Handles.
!The construction of the Type R-3 bomb release handle for use with the Type G-4
bomb rack has been completed.
* * * *
Safety release handles have been built for use on the C-2 airship which is being
equipped with Mark XVI and Mark XIX bomb racks. (See foot note.)
Bomb Racks.
Metallic beams for the Mark XVI and XIX external bomb racks have been re­worked
and tested. Six sets of beams for each of these racks are under construction.
Bomb Sighting Devices.
Pilot Director Type X-2 has· been flight tested and modified to operate on a bat­.
tery of changeable voltage, always indicating a positive zero reading when the ground
course is aligned on the target.
The device is incorporated in the new bomb sights "D-1", "X-4", and "X-7".
Flight tests in all three of these have given excellent line results when approaching in
random directions without regard to wind. .
* * * *
The type D-1 bomb sight has been flight tested with satisfactory r,esults and is
now in experimental production for service tests.
* * * *
The bomb sights, Mark lA Army type and Mark III Navy type, have been stab­ilized
and provided with pilot directors. These modifications are known respectively as
stabilizers, types X-7 and X-4. The old pilot director formerly included in the Navy
sight never gave satisfactory results.
Recent flight tests of the modified sights have given better results than were
formerly obtained with the unstabilized sights. Experimental production is in progress
on both types.
CORRECTION:- Technical Orders No. 23, page 16, under "Bomb Racks for C-2 Airship Car,"­Mark
XI should r ead Mark XIX.
14
I
New Design-Armament
Flight tests of the Goerz bomb sight are being conducted for comparison of this
sight with later types.
* * * *
A bomb sight accessory (type X-2), built by the Sperry Gyroscope Company for
the Engineering Division, has been tested.
A design is in progress combining this accessory with a pilot director, in one in­strument,
to automatically hold the pilot in a correct line of flight whenever the bomber
has aligned the pilot by means of a pilot director. ·
* * * *
A camera obscura has been installed in the roof of the Armament Section lab­oratory
with wireless receiving set for bomber's signals. Flight tests of bombing appa­ratus
are in daily operation.
GUNS
Cannon.
An automatic sight for cannon has been constructed and is undergoing test. This
design is a compensated sight for use on the Engineering Division GA-1 airplane and is
known as type D-1.
* * * *
Type B mount for cannon is being assembled for experimental test with a Bald­win
37 m.m. cannon. The cannon is flexibly mounted on a movable ring. A slight move­ment
of the cannon up or down or to either side makes an electrical contact which
causes the movable ring to move in the desired direction. Power is furnished by a small
electric motor.
Synchronizers.
Type D-1 electrical synchronizer is now being constructed for service test. A
solenoid trigger motor is operated by a special magneto. The operating control con­sists
of a small electric button switch in the pilot's control switch.
15
New Design
EQUIPMENT
GENERAL
Night Flying.
During the month of June, several night flights were made to determine the
visibility of the General Electric wobbling mirror searchlight and the Sperry vertical 60-
inch searchlight. The results indicated that lights of this type will not be of much value
on a clear night when flying is good, because the searchlight ray is then not clearly vis­ible
when seen from a considerable distance. This is due to the line of sight being
practically perpendicular to the ray. However, on nights when there are high clouds, .
the vertical ray lights will no doubt give good yisibility over a considerable range. The
tests on these searchlights will be continued.
* * * *
It has been proposed to mount a searchlight upon a revolving table in such a
manner that the rays will be thrown a few degrees above the horizontal. The table
will then be revolved at a constant rate causing the beam of light to be directed more or
less toward an airplane approaching from any direction. If the direct light from this
beam is not seen by the approaching airplane, the revolving beam will at least be more
noticeable than the vertical one.
INSTRUMENTS
Compact Instrument Units.
As a result of the successful arrangement and illumination of the tachometer
compact instrument units mentioned in Technical Orders No. 24, page 18, a new unit con­sisting
of the water thermometer and the oil and fuel pressure gages has been con­structed
and installed on a Martin Bomber airplane for test.
This unit occupies a space 6%." x 2% " on the' instrument board. The dial is trans­lucent
and is illuminated by an electric light, placed inside the case, which gives suffici­ent
illumination for taking readings at night without blinding the pilot. The leads for
the thermometer, however, fix within certain limits, the usefulness of the instrument.
Plight Indicators.
These instruments differ from the previous so-called flight indicators in that they
indicate the turning motion of the airplane in pitch, yaw, and rolling, and also the atti­tude
of the airplane in pitch or roll. The former flight indicators consisted of a turn in­dicator
combined with a lateral indicator while the present instrument is made by com­bining
these two indicators with a pitch indicator. The pitch indicator is a combina­tion
of an air-driven gyroscope and a pendulum. The gyroscope will give an instantan­eous
indication of any change in the longitudinal attitude of the airplane and the pen­dulum
will show the longitudinal attitude of the airplane after the change has taken
place.
16
New Design-Equipment
Work has been started on the construction of twenty-two flight indicators by
the Pioneer Instrument Company. The first models will be tested at McCook Field and
the succeeding ones will be service tested on airplanes flying on the airway. Following
a completed and successful service test, the instruments will be standardized for ser­vice
use.
Oxygen Regulators.
The fourth model of the Prouty type, oxygen regulator, manufactured by the
Precision Instrument Company, has been received and tested. This in,strument gave
regulation within the specification limit except for cases where the flask pressure
dropped below 50 atmospheres.
* * * *
A hand-operated oxygen regulator, received from the Bastian-Blessing Company,
has given promising results on preliminary tests. This regulator makes use of a con­stant
orifice and a constant pressure that is maintained by one adjustment of the re­ducing
valve. In other words, the reducing valve will deliver a stated quantity of oxy­gen
per minute, regardless of the pressure in the flask. It is therefore possible in alti­tude
flights for the pilot to control and to note on a dial the delivery pressure of the
valve and consequently the amount of oxygen that he is receiving.
PHOTOGRAPHIC
Motion Picture Cameras.
An order has recently been placed for the purchase of four hand-held, electric-ally-
operated motion picture cameras, each of which is to be equipped as follows:
(8) Magazines with carrying case.
(1) Two-inch lens.
(1) Three-inch lens.
(1) Six-inch lens.
(1) Negative lens view-finder.
The electric motor will operate on a 6-volt current and is to be mounted directly on the
camera.
17
EXPERIMENTATION
RESUME OF ENGINEERING DIVISION
SERIAL REPORTS
S erial Reports rnarlcerl -with cin asterisk (*) will be
issiwd by the Chief of Air Service as ''v:lir S ervice
Inf or1nation C irciila1 ·s. ''
AIRPLANE SECTION _
Static Test of Loening PA-1 Airplane. ,:,serial No. 1902
The Loening P A-1 airplane, built by the Loening Aeronautical Engineering
Corporation of New York, is a single-seater pursuit biplane, propelled by a 350 h.p.,
9-cylinder, air-cooled Wright radial engine.
A complete account of the test, general arrangement drawings, and views of the
airplane are given.
Wind Tunnel Test of Model of Streamline Mudguard
for Martin Bomber. Serial No. 1905
A resistance test was made on two scale models to determine the benefit of
streamlining the landing gear of the Martin Bomber; one model representing the pres­ent
landing gear, and the other a similar gear with streamlined shape.
The effect of streamlining decreased the resistance 37 % , which amount, when
applied to a complete scale model of the airplane on which the landing gear represents
12% of the total resistance, would make a net decrease of 4% in the total resistance.
The net gain is equivalent to a capacity of two additional passengers.
Test data, views of model, and apparatus are appended.
18
Experimentation-Serial Reports ·
Wind Tunnel Test of Fokker Monoplane, Type D-8. Serial No. 1911
The report covers the test of a 1/18th scale model of the airplane in the M. I. T.
wind tunnel. In addition to the usual tests for determination of tail plane settings,
the wing alone was tested at air speeds of thirty and forty miles per hour for lift, drag,
L/D and center of pressure travel.
The form of the lift curve is quite unusual and suggests some connection be­tween
the maintenance of a high lift at large angles and the remarkable maneuverabil­ity
of the airplane. It suggests further that the maneuver of "hanging on the prop"
for which the Fokker airplane is noted, may be actually normal flight at an angle of
attack of approximately 60° and not the result of a helicopter action primarily.
Impact Test of Steel Landing Gear for Air Mail Service
DH-4 Airplane. Serial No. 1918
A landing gear which was submitted for test by the Air Mail Service, proved un­~
atisfactory.
The chassis was made entirely of metal with steel struts of elliptical section
mounted on a bronze casting having projecting arms upon which the shock absorber
cord is wound, and guide ways on which the axle shock absorber casting moves.· The
metal streamlining for the axle is riveted at each end to a bronze casting which in turn
is attached to the strut casting by means of two cap screws. This streamlining forms
the cross member of the gear for carrying either compression or tension loads.
Static Test of Engineering Division PG-1 Airplane
(Built by Aeromarine Plane & Motor Co.). *Serial No. 1919
The airplane is a biplane with an armored fuselage and fabric-covered wings of
wood construction. The tail surfaces and rear section of fuselage are of steel construc­tion
with fabric covering. It is powered by a Wright "Cannon" engine, type K-2.
Structural details, test results, and views of the parts are appended.
Static Test of Thomas-Morse MB-6 Airplane. ,:,serial No. 1920
The airplane is a single-seater, racing type biplane of wood construction and is
fitted with a high compression eight-cylinder Wright 400 h.p. engine.
The report gives structural details, test results, and views of parts under test.
The performance and views of the airplane were published in Technical Orders No. 22.
Wind Tunnel Test of Dayton-Wright (DW-9) Aerofoil. Serial No. 1930
A model aerofoil was constructed by the Dayton-Wright Company and submitted
to the M. I. T. for test by the Engineering Division.
The results indicated a good lift-drag ratio which is due to low drag ·rather than
to high lift. Test results and curves are given in the report.
19
Experimentation-Serial Reports
ARMAMENT SECTION
Tail Gun Installation for Pursuit Type Airplane. Serial No. 1922
A mount for a 30 calibre Browning gun was designed for use in a single-seater
pursuit airplane to permit the gun to be fired directly to the rear and in the line of
flight of the airplane. A periscopic sight for use w,ith this installation was designed to
accommodate the pilot's vision to the rear without turning around. The sight was
mounted upon the cowl of the airplane with its eye piece along side of the eye piece of
the Unit sight.
Although this installation functioned satisfactorily, the mounting of the gun, in
this type of airplane at a point so far from the center of gravity would necessitate a.
complete redesign of the airplane and, consequently, could not be recommended for this
purpose. Furthermore, the recent development of the Thompson sub-machine gun, a
smaller and lighter gun than the Browning, has provided a gun that is more suitable
for this kind of installation in a pursuit airplane.
Views of the Browning gun tail mount and the periscopic sight are shown.
Development of Machine Gun Synchronizer-Type C-3. Serial No. 1927
The Nelson gun control has been modified to permit the flexible use of the im­pulse
cable, thereby facilitating the installation of fuel tanks, fire walls, cowling, and
other parts of the airplane, which are usually located between the gun control gener­ator
and the gun mount.
Part I of the report contains the description and views of the new impulse cable
while Part II gives the other changes made in the synchronizer in accordance with recom­mendations
contained in Part I. Views of impulse cable with attachments, the instal­lation
for the test, and targets showing results of firing tests al'e given.
Test of Sperry Mechanical Compensating Machine Gun Sight. Serial No. 1931
This sighting mechanism consists of a finder telescope mounted upon the top of a
flexible machine gun in such a manner that the telescope is moved mechanically from
side to side in a horizontal plane to compensate for the speed of the airplane upon
which the gun is mounted and for the range , of the target. The angular compensation
is obtained by a mechanical translation of the uniform movement of the gun by means of
a flexible shaft rotated by the relative movement of the two rings comprising the base
of the ring mount, while following the target in flight.
The device was mounted upon a 30 calibre Lewis gun in a Type A ring mount
for test. The magazine of the gun was replaced by an Eastman automatic gun camera.
The tests showed that this sight did not satisfy the requirements as well as the
standard wind vane, bead and ring sights. This conclusion is based upon the complica­tion
of the mechanism, the lag at long ranges, and the fact that it requires manual ad­justments
while sighting through the telescope.
20
Experimentation-Serial Reports
EQUIPMENT SECTION
Test of Porox Storage Battery. Serial No. 1913
This is a lead-acid type battery formed by four transparent celluloid jars ce­mented
together making a single battery unit of eight volts. Each jar contains two
positive and two negative plates, each of which are about 11/ 64 inches thick. Perfor­ated
celluloid separators with narrow celluloid strips, running vertically, cemented to
them, provide an average spacing of 3/ 32 inches between the plates. The space at the
bottom for sediment is 5/16 inches deep. An electrolyte of 1.225 specific gravity when
fully charged, is used.
The battery which is the same weight and capacity of the standard ignition bat­tery,
proved satisfactory for use where small capacity is needed but on account of the
lack of non-spill features and the fire hazard dormant in the unprotected celluloid cells,
it was considered unsuitable for aircraft use. Views of the battery and the discharge
curves are given.
Test of Cincinnati Aviation Storage Battery
(Types AC-111 and AC-212) Serial No. 1914
Upon test, this battery was found to be the best aviation battery available for
starting and lighting purposes for airplanes owing to its compactness, its light weight
relative to capacity, the large amount of current produced for starting purposes and the
fact that it can be completely inverted without spilling any electrolyte. It can also be
stored "bone-dry" for twelve months without injury.
The report gives assembly drawings of both types, discharge curves, and photo­graphs.
Test of Unit Flying Suit. Serial No. 1916
A flying suit comprising in one unit, the coat, trousers, moccasins, gloves, hel­mit,
and mask, was made by the Elder and Johnston Company of Dayton, Ohio, for the
Engineering Division.
/
The outer body covering was made of rubberized cotton moleskin and lined with
nutria fur. Openings which were closed by means of hookless fasteners were provided
in the back, the lower part of the sleeves and in the back of legs. . The moccasins were
lined with sheep skin with the wool attached. The regular fur-lined combination mit­ten
type gloves were used. The helmet and mask were the standard Spalding, nutria
fur-lined face helmet attached to the body by a silk collar of bellows construction.
The suit proved unsatisfactory for service use as it could be worn only in the cold­est
weather and was unweildy and difficult to put on or take off without assistance.
Views of the suit are shown.
Life Test of Turn Indicators. Serial No. 1935
In order to determine the durability and operating characteristics of the Sperry
1\4:ark I model B, and the Pioneer turn indicators, the instruments were submitted to a
21
Experimentation-Serial Reports
test covering 1,208 hours of continuous use. Two of the instruments, the Sperry No. 3
and the Pioneer No. 2, were still serviceable at the end of the run. A detailed account
of the test and views of the internal mechanism of the indicators are given.
FL YING SECTION
Performance Test of Fokker V-40 Pursuit Airplane. Serial No. 1900
This airplane, built by Anthony H. G. Fokker qf Holland for the Engineering Di­vision
and recently designated the "Fokker PW-5", is a type I, single-seater pursuit
monoplane equipped with a "Wright "H" 300 h.p. engine. The performance and views
were published in Technical Orqers No. 24.
Service Use of Air Speed Conversion Monoi?;ram. Serial No. 1923
The air speed conversion monogram was originally constructed as an aid to the
computation of data for performance reports and represents, graphically, the determin­ation
of true air speed by the application of the coefficient of correction for density at
any altitude to the indicated air speed. ·
An air speed conversion chart with directions for its use is appended to the
report.
MATERIAL SECTION
Investigation of Physical · Properties of Fanosite. Serial No. 1906
Fanosite is an aluminum base alloy, manufactured by the Aterite Company of
New York. The grade of Fanosite submitted for the test is an alloy suitable for pur­poses
where strength is required and not the one the manufacturer recommends for
use in resisting the corrosive action of acids.
The results obtained in the investigation showed that the alloy did not come
under Air Service Specification No. 11023 and that further tests were not warranted.
Chrome-Molybdenum Steel. Serial No. 1910
The investigation was made to determine the physical properties of chrome­molybdenum
steel. The test specimens which were manufactured by the Halcomb Steel
Company of Syracuse, N. Y., by the Electric process and annealed at the mill, were
subjected to tension, torsion, compression, shear, impact, and hardness tests, each test
being made for each of the following conditions: "as received," normalized, quenched in
oil at 1600° F. and drawn at 400, 600, 800, 1000, and 1200° F. respectively. In general,
the results indicate-
(a) A general increase in all strength values with decrease in drawing temper­atures.
(b) Proportional limit in tension decreases with decrease in drawing. temper­atures
under 800° F.
22
Experimentation-Serial Reports_
(c) An increase in elongation and reduction in area with increase in drawing
temperature.
Complete test results, metallography and views of test specimens and their mi­crostructure
are given.
I
Physical Properties of Chrome-Nickel Steel (No. 3330 Steel). Serial No. 1912
The physical properties as determined in this investigation indicate that-a.
There is no practical difference in the tensile strength or hardness of speci­mens
quenched in oil and those drawn to 200° F. Drawing at higher tem­peratures
causes a uniform decrease.
b. The proportional limit increases with decrease in drawing temperature to
600° F., after which it decreases.
c. Elongation is practically constant below drawing temperature of 800° F. with
considerable variation in reduction in area.
d. Impact values do not change much below 600° F.
e. Tensile strength increases with decrease in drawing temperatures down to
200° F.
Complete test results, views of the testing apparatus and specimens, and the
microstructure of the steel are given.
Organic Coatings for Duralumin-Part I. Serial No. 1917
This investigation is of a preliminary nature to determine (1) the necessity for
a coating to protect duralumin from atmospheric corrosion, and (2) the best organic
coating of several samples which were submitted by manufacturers, in case some protec­tion
was necessary. Particular attention is paid to the corrosive action on duralumin
of the variety of pigments used in the primers and enamels which were tested.
As a result of the exposure of the samples from six to fourteen months on ex­posure
racks and wing surfaces of service.airplane, it was concluded that a coating fo1·
duralumin is necessary if atmospheric corrosion is to be prevented.
The results of the exposure test are given in tables and photographs. A list of
coatings is given also.
Heat Treatment Bath-Sodium Chloride, Sodium Carbonate, and
Sodium Cyanide. ,:,serial No. 1924
The determination of the suitability of a heat treating bath composed of sodium
chloride and sodium carbonate with and without the addition of sodium cyanide was
made in this investigation.
It was found that low carbon steel was slightly carburized on the surface by the.
bath after cyanide was added while the high carbon steel was ,slightly decarburized in
the same bath. This suggests that the carburizing action would be nil on a steel of in-
Experimentation-Serial Reports
termediate carbon content and that for any particular grade of steel, a cyanide content
in the bath could no doubt be arrived at, which would have a neutral effect upon the
carbon of the steel.
Adaptability of Hyde Welding Process to Steel Engine
Cylinder Construction. *Serial No. 1925
It was found in this investigation that the welding action obtained by this pro­cess
upon the structures of No. 1020 and No. 1040 steel is satisfactory in regard to the
formation of a uniform bond and the effect on structure. The Hyde process possesses
also some distinct advantages over other methods of joining steel for high strength such
as the torch and arc welding or torch brazing processes, in that it shows an absence of
local overheating, gives a more uniform joint, and possesses freedom from warpage due
to localized heating or non-uniform heating.
POWER PLANT SECTION
Report on Blower for Cooling Air-Cooled Cylinders
on Test Stand. ,:,serial No. 1843
The blast for cooling air-cooled cylinders on the test stand at McCook Field is
furnished by a "Sirocco" air blower manufactured by the Americ~n Fan and Blower Co.,
Detroit, Michigan. The blower which is driven by a 100 h.p. electric motor, is fitted
with a 20-inch outlet and a movable duct for directing the blast to the cylinder. A cy­lindrical
intake admits either outside of inside air or both, the velocity of the air blast
being :regulated by the size of the intake orifice.
The tests sho.wed that the mean air velocities at the discharge duct of the blower
varied directly as the diameter of the orifice with the outside air intake open and that
the velocity of the blast increased noticeably with larger orifice openings and the ad­dition
of the inside air intake.
Fifty-Hour Endurance Test on Liberty "1.2" ,Engine (1921 ~odel). Serial No. 1844
ment:
This model is the standard Liberty "12" engine fitted with the following equip-
Standard pistons with oil return grooves.
Stub tooth gear trains.
Gear type fuel pump.
New oil pump with Stryker separator.
Oil vent connection.
Delco 12-volt ignition with Buzzer starter.
Standard Zenith carburetor.
Automatic altitude control.
In connection with the test, the engine was equipped with exhaust valves of
tungsten steel and Oakley Monel metal for comparison. The Monel metal valves showed
24
Experimentation-Serial Reports
little signs of oxidation and gave better results than the tungsten steel valves. A de­tailed
account of the performance of the Monel metal valves is being compiled.
Complete performance data of the test with views of the valves, pistons and
other parts are appended to the report.
Endurance Flight Test of Mercury-Cooled Valves
in Hispano-Suiza Engine. , Serial No. 1851
A test was conducted for determining the relative merits in regard to oxidation,
conductivity of heat away from head, and general performance of solid stem exhaust
valves and hollow stem exhaust valves partially filled with mercury. ·
The mercury-filled valves, which are manufactured by the Fan Steel Products
Co., of Chicago, are made of a low tungsten steel body with a large cavity 2% inches
long drilled into the stem through the head of the valve. The cavity is filled with an
amalgam of lead, tin, and mercury and sealed by a retaining plug in the head.
Two sets of valves, each set consisting of four standard and four mercury-filled
exhaust valves, were installed in Hispano-Suiza engines and tested. The results indicated
that the mercury-filled valves had no advantages over the standard ones and would re­quire
considerable improvement in their mechanical construction.
Fifty-Hour Endurance Test on Curtiss "CD-12" Engine
(Army and Navy Runs-First Engine). Serial No. 1853
The Model "CD-12" is a direct drive, twelve-cylinder, water-cooled, Vee type en­gine,
consisting of two banks of six cylinders each with an included angle of 60° between
the banks. It is essentially the same in construction as the Curtiss "C-12" geared en­gine,
a complete description of which is given in Serial No. 1780 (Technical Orders No.
24, page 36) .
Two tests were made at McCook Field; a ten-hour acceptance run was conducted
by the Navy Department prior to a fifty-hour endurance run by the Engineering Divi­sion.
The results of the first test in which the engine was fitted with low compression
pistons (5.23 :1) and run at a normal speed of 1800 r.p.m., were satisfactory. The Army
run was madf with 5.37 :1 compression pistons and at a normal speed of 2000 r.p.m.
The general performance of the engine was satisfactory but definite conclusions
as to reliability and durability are withheld owing to the changes and replacements of
newly designed parts.
Variation in Performance of Hispano-Suiza Model "E" Engine
With Degree of Throttle Opening. '~Serial No. 1854
The investigation was undertaken in order to determine the variation in per­formance
of a typical airplane engine at given throttle openings over the entire speed
range. Reliable data were obtained on the Hispano-Suiza Model "E" engine by using
an intake. air heater to maintain the temperature of air supplied to carburetor at ap­proximately
95° F. It was possible to reproduce given conditions and check the perfor­mance
within certain limits.
25
.Experimentation-Serial Reports
Curves of the power output obtained at given throttle openings over the entire
speed range, the specific fuel consumption, and views of the intake air heater are given
in the report.
Fifty-Hour Endurance Test on Packard "lA-825" Engine. Serial No. 1855
The report gives in detail a complete account of the standard endurance run and
recommendations for the improvement of the design.
The Model "lA-825" eight-cylinder engine is a modification and enlargement of
the Packard Model "lA-744" described in Technical Orders No. 16. The characteristic
features of these engines are as follows:
Model "lA-825"
Cylinders ______ _____ _____ ______ _____ ________ ___ ___________ eight, two rows, 60° vee
Bore and stroke ---------- --- -- --- -- ----- ---- ---- --- 5x51/1 (inches)
Displacement _________ ___-_ _______ __________ ___ ______ __ .825 cu.in.
Compression ratio ----- ---- -- ------ -- -·------ -- --- 5.02: 1
Normal speed __ _______ ___________ ______ ______ ________ 1800 r.p.m.
Horse power at normal speed. ____________ 224
Fuel consumption in lbs. per h.p.hr. ___ 0.5
Carburetor ______ _______________ __ ___________ __ ____ __ ____.P ackard Zenith US-54
Ignition -- --- -- ---- ------- -- ------ --- ----- ---- -- -- -- --- ·--- (2) Dixie Magnetos
No. 860
Model "lA-744"
eight, two rows, 60° vee
43/ 1x514 (inches)
744 cu.in.
5.02:1
1800 r.p.m.
183
0.48
Packard Zenith
(Double Venturi)
Delco
The cylinder, carburetor, and many other parts of the Model "lA-825" are also
interchangeable with those of the Model "lA-1237," twelve-cylinder engine.
Power curves, test results, and views of the engine are given in the report.
26'
FOREIGN DEVELOPMENT
FRANCE
AVIATION MATERIAL
The development of French militllrY aeronautics, from the time of its ongm in
1914, has been rapid, particularly during the latter part of the World War. Since then,
the creation of military aviation material has been prngressing actively along well-de­fined
lines under the direction of the Air Ministry.
The pres'ent aeronautical policy is determined by a joint conference between the
Ministry of War ,,.vhich decides upon. the military requisites of the service, and the Min­istry
of Public Works, which through its subordinate bureaus represented in the con­ference,
presents the technical side.
These bureaus, four in number, are the Servi':e of Aerial Navigation, the Na­tional
Bureau of Military Meteorology, the Service of Manufacture for Aeronautics
(S.F.Ae.) and the Technical Service for Aeronautics (S.T.Ae.). The design and manu­facture
of aviation material for all purposes of the state are controlled through the two
last-named bureaus. The S.T.Ae performs the functions incident to the study, experi­mental
construction, and testing of new airplanes, engines, armament, equipment, and
other aeronautical material.
The trend of airplane design has been along the line of the' all-metal airplane as
may be seen from the discussion of the types presented in this article. These types have
been recently laid down by the conference .referred to above and represent the latest
policy and tendencies in airplane development.
FRENCH MILITARY AIRPLANES (LATE TYPES)
The airplanes, herein described, are for the most part new experimental types in
the course of study, design, or construction. A few have been completed and accepted
for production for the service. The general characteristics only will be given at this
time as the majority of the designs are not sufficiently . advanced to make technical de­tails
available.
27
.Foreign Development-France
PURSUIT AIRPLANES
(Single-Seater)
Symbol-C.
Gourdou C 1 (Hispano-Suiza 300 h.p. Engine-Rateau).
This model is a single-seater monoplane for high altitude pursuit work, the de­sign
and construction of which are in progress. The engine is equipped with the Rateau
turbo-compressor or supercharger. The details of construction are not yet available.
Wibault C 1 · (Hispano-Suiza 300 h.p. Engine-Rateau).
The Wibault airplane which is designed for pursuit at high altitudes is a single­seater,
all-metal monoplane constructed of duralumin and steel. The wing is patterned
after: an approved design patented by M. Wibault in 1920. Its aerodynamical character­istics
have been carefully studied in the aerodynamical laboratory at St. Cyr. The en­gine
is equipped with the Rateau supercharger.
The airplane has a span of 37 ft. 4 in. and a length of 26 ft. 4 in. and is designed
for a useful load of 990 lb. For commercial purposes, it may be easily converted into
a mail carrier with a capacity of 330 lb. of mail over a range of 620 miles.
PURSUIT AIRPLANES
(Two-Seater)
Symbol-CAp.
Borel CAp2 (Hispano-Suiza 300 h.p. Engine-Rateau).
A new airplane recently completed is the Borel two-seater pursuit biplane de­signed
for pursuit at high altitudes and long distance reconnaissance. The principal
characteristics are as follows :
. Span _________________ _________ ____ ___ ___ __ __ ____ ____ ______________ ________ ___ ___ 37' 4311,"
Length -------- ---------- -------- -- -- ------ --- -- ----- ----- -- --- __ ________ __ __ 23' 31/2"
Wing chord -·· ·---- --·- ---- ----- -- ------ --- -·-- -· ··-------- ------- ------ 5' 3"
Wing area -- ------------- ------- -·····-- --·· ··-·- ······-··--·-·· ·-----·-----360.5 sq.ft.
Gap ···---- ---··---- ---- ---------- --- ----·- ------- ·· ····----------- --- -- -- -- -- ---- 4' 11"
Weight empty ------··--·····--·· ---- --- -· ···---··-- ··----- --- -- -- -----'.1771 lbs.
Weight loaded ----- --- -- ··------ ----- --- ----·-··· -·- ·· __ ______________ ___ 2915 lb.
Useful load ····················--·---·- -- --· ······-······-- ----- ---- -------1144 lb.
Wing loading --··········-·····-·-········--······---······- ·--- ------- ·-8.1 lb./sq.ft.
Power loading ····----- -------------- --- -···· ···········-------- ---- ------9.68 lb. / h.p.
28
Performance :
Altitude
(feet)
0
6,500
9,840
16,400
19,680
22,960
26,890 A. C.
Climbing Time
(minutes)
--- - - -
0
5.6
9
18.3
25
Gourdou CAp2 (Hispano-Suiza 300 h.p. Engine-R~teau).
Foreign Development-France
Speed
(m.p.h.)
161.4
155.2
150.9
139.7
130.4
113
Construction has been started on a two-seater monoplane of this type. The Ra­teau
supercharger is used.
Hanriot CAp2 (Hispano-Suiza 300 h.p. Engine-Rateau).
Construction is in progress on this model, the details of which are not available
at present.
Potez CAp2 (Lorraine 370 h.p. Engine-Rateau).
This model is a two-seater biplane on which construction has started. No details
are available.
S.P.A.D. CAp2 (Hispano-Suiza 300 h.p. Engine-Rateau).
The development of this two-seater biplane is in progress-details are not yet
available.
ARMY CORPS OBSERVATION AIRPLANES
(Two or Three-Seater) ,
Symbol-A.
Breguet 19 A-2 (Breguet-Bugatti 450 h.p. Engine).
This airplane is a two-seater biplane design with dual control. The cellule is of
the single interplane strut type with the upper wing of large area and over-hang. The
lower wing is smaller in chord and area. A semi-thick wing section is used.
The engine installation permits the use of either the Renault twelve-cylinder, 450
h.p. engine or the Bugatti sixteen-cylinder, 450 h.p. duplex engine.
29
Foreign Development-France
Main Characteristics and Performance:
Span (upper wing) ______ __ , _________ _______ ___________ ______________. 45' 6"
Span (lower wing) ________________________ _____________ ________ _____ 31' 3"
Length ____________________________ ____ __ __ __ __ __ _______ _______________________ 30' 2''
Height "----- ----- ----- ---=----- -- -- ------ ------- ----- -- --- ------- ------ -------10' 10"
Wing area __________ ____ ___________________________________________________.4 84.4 sq.ft.
Weight empty ----"---- ------ -- -- -- --------- ---- ----- -- ------- --- --- ----2541 lb.
Useful load ___________________ ____________ ___ ___ _____________ ______________ 1650 lb.
Speed at ground _______ ___ __ _________ ___ ___ ________ _________________ 142.8 m.p.h.
Absolute ceiling ___ __ __ _________________ ____________ ___________ _________ 26,400 ft.
Endurance _____ _____ _____________ ______ _______ ___________ _________ _______ __ 4 hours
Farman A-2 (Salmson C.U. "Z-9" 250 h.p. Engine) .
The Farman firm built the first airplane of this design in 1921. The tests were
made at Toussau. It is a two-seater biplane of entirely metallic construction and is de­signed
for observation and surveillance work.
Characteristics :
Span ____ _______________ __ _________ _________________________ ___________ ___ ___ ____ 39' 7"
Length ------- ---- -------- ------ -- ---- ---- -- ------ ---- ----- ------ --- ------ --- --29' 8"
Height ________ __ ___ _____________ ___ __ ________ _,_ ______________________ ___ __ ____ 10' 9"
Weight empty -- ------ -- ------ ------- -- ----- ----- ___________________ ___ 1970 lb.
Weight loaded _______ ______ _________ ___ ____________________________ _______ 3190 lb.
Useful load --- ---- --- --- ---- ---------- ----- ____ ____ __ ___ ___ ______________ 1220 lb.
Wing area ---- -- ----- ----- ------- ---- ------- ----- ---· -- ----- -- ------------- 400 sq.ft.
Wing loading ----- -- ---- -- --- ---- --- --- -- --- -------- --------------- ------ 7.97 lb./ sq.ft.
Performance (first airplane):
Altitude
(feet)
6,560
16,250
19,680
21,780 A. C.
Climbing Time
(minutes)
----- --
7.5
28.5
Speed
(m.p.h.)
117.2
99.8
Endurance _____________ : __ : _____ ___ __ ________ __ ________ ____ ______ ___ ___ .4 hours
The second airplane of this model was made lighter than the first with the wings
non-staggered and the cockpits moved farther back. No details of construction are
available.
Liore-Oliver A-3 Leo 7 (Two Hispano-Suiza 300 h.p. Engines).
This is a late model, two or three-seater biplane of metallic construction r ecently
t ested at Villacoublay.
30
Foreign Development-France
Characteristics:
Span ·······------ ------- ----- -- -------- ------------- ---- -- -- --- -----------------60' 5/16"
Length __ ____________ __________________________ __ __ ________ ___ __ , _____________ 38' 1-3/ 16"
Height --- -------- -----------------------------___ ___ ________ __ __ _____ ____ _____ 12' 3-5/8''
Wing area ____________ __ ___________ ________ _____ _______________ __ __ _________ 700 sq.ft.
Weight empty ----- -------------- ------- -- ------··--··----- -------- _____ 3696 lb.
Weight loaded ________________________ _______________ __ ___ ____________ __ __ 6380 lb.
Useful load _________ ______ ___ ___________ ____ ___________________ ____________ 2684 lb.
Wing loading ------ ---------- ----- ---------------- --_____ ________________ 9.11 lb./ sq.ft.
Power loading ______ ____ ________________ __ ______________________ __ ____ ____ 10.63 lb./ h.p.
Performance :
Speed at 16,400 ft. ___ ______ ___ ____ ______ __ ______________ ______ __ ____ 117 .9 m.p.h.
Absolute ceiling -------- -- --- -- ----------------,---- ----·----- -------- --23,000 ft.
Endurance --------------------------------------------------------- --- -- --- -4 hours
Potez A-2 (Lorraine 370 h.p. Engine).
The Potez A-2, recently completed, is designed to replace the old type Salmson
and eventually the Breguet airplanes. It is a two-seater biplane of wood and fabric
construction.
BOMBARDMENT PROTECTION AIRPLANES
(Multi-Seater)
Symbol-Bpr,
Latecoere Bpr 3 (Four Salm.son CU "Z-9" 250 h.p. Engines).
The airplane is a three-seater, all-metal biplane having a metallic hull or fuselage.
The construction is about completed. ·
The purpose of this type of airplane is to protect day bombing airplanes.
NIGHT BOMBARDMENT AIRPLANES
r.i.'wo-Seater).
Symbol-En.
Wibault En 2 (Renault 600 h.p. Engine).
Two airplanes of this type which is to replace the Farman-50, were constructed.
They are two-seater biplanes of duralumin and steel construction. The Wibault wing is
used. The airplane has a large capacity for 200 to 400 lb. bombs and may be converted
with slight changes into a passenger transport having a capacity of twelve passengers,
the cabin being 14.7 ft. long, 5.2 ft. wide, and 5.9 f( high.
31
Foreign Development-France_
The principal characteristics and estimated performance are as follows:
Span .......................... , ..................................... ............. 55' 9''
Length ............... ............... ............................. ............. 41' 10"
Height ...................... ........................................... ....... 16' 6"
Span of upper wing ................ ................... ......... ..... .49' 101)1,"
Chord (upper and lower) ............................... ......... 9' 95/s"
Wing area ... ... ................ .... .... .................................... 995 sq.ft.
Weight empty ......................................................... .4440 lb.
Weight loaded .............. ... .... ......... ......... ................ ..... 9500 lb
Useful load ............................. .................................. 5060 lb.
Speed at 6,560 ............................................ ........ ...... 124.2 m.p.h.
Absolute ceiling ............... ...... ................................... 16,400 ft.
Endurance ........................................................... ...... .4 hours
LONG DISTANCE NIGHT BOMBARDMENT AIRPLANES
(Multi-Seater)
Symbol-En.
Farman En 4 (Four Lorraine 370 h.p. Engines).
This airplane was originally designed for Panhard engines but_ has been rede­signed
to use twelve-cylinder Lorraine engines which are placed in tandem on each side
of fuselage. It is a multi-seater, carrying a crew of four. ·
The principal characteristics and estimated performance· are as follows:
Span .... ....................................... ............ .......... ..... ...... 113' 10"
Length ............... ...................... .... ..... ....... .......... ... ...... 72' 7"
Height ...................................... .. , ....... ..... ............... ..... 24' 9"
Wing area .................. ................ ... ........... ... ...... ......... 3,240 sq.ft.
Weight empty ................ .................... ...................... 11,660 lb.
Weight loaded .................... ...... ....... ................ ...... ..... 22,550 lb.
Useful load ...................... ..... ..... ...................... ......... 10,890 lb.
Wing loading ....... .. .. ........ ........ . .. ............ ................. 6.96 lb./ sq.ft.
Speed at ground ............... .... ... . ...... ........ .... ..... ......... 100 m.p.h.
Absolute ceiling ............................. ...... ...... ...... ......... 15,000 ft.
Endurance .......................... .... .................. .... .............. 5 hours
Henri Paul Schneider En 3 (Four Lorraine 370 h.p. Engines).
Construction is in progress on a three-seater biplane for night bombing.
32
TRAINING AIRPLANES
Symbol-E and ET.
Caudron C-27 E (LeRhone 80 h.p. Engine).
Foreign Development--,-France
The Caudron training airplane (Ecole-E) is a two-seater biplane with ailerons on
upper wing only. It is equipped with a two-wheeled landing gear h,w ing a Sandows
shock absorber. A skid to prevent nosing-over in landing is provided beneath the fu se­lage,
the front and rear ends of the skid being suspended from the fus2lage by vee struts
while the center of the skid is attached to landing gear axle.
The principal characteristics and performance are as follows:
Span .... ........ ........................ ...................... .... .............. 39' 4"
Length ······· ········ ············---~······· ................................ 23' 5"
Height ....................... ................. ................................ 9' 10"
Sp:rn of lower wing ..... .. ... , .... ........ ........... .. ......... ..... 16' 8"
Wing chord (upper and lower) .......... ...................... 4' 11"
Wing area ...................... .......................... .. ........... .. ... 374.6 sq.ft.
Weight empty ..... .. ....... ................................ , .. ......... 1038.4 lb.
Weight loaded .. ........ ........ ........ ................ .. ............... 1601.6 lb.
Useful load ........... .... ...... ........................................... 563.2 lb.
Speed at ground (maximum) .. ....... ... ....... .......... ..... 66 m.p.h.
Speed at ground (minimum) ..... ............ ................. 50 m.p.h.
Climb to 6,560 ft .... ................................................. 19 min.
Service ceiling ..................................... ............ ......... 11,380 ft.
The airplane has good stability and responds quickly to controls but it is hard to
pilot during heavy weather. The landing gear is too flexible, allowing wing tips to strike
ground while machine is rolling.
Farman 80 ET 2 (Hispano-Suiza 180 h.p. Engine).
The airplane which is a two-seater biplane with dual .control, was originally
equipped with a Renault 190 h.p. engine but has been recently modified to accommodate
the Hispano-Suiza engine. The modifications also include a reduction in wing area of
75 sq.ft. and the shortening of the distance between the pilot and student. The landing
gear has a wide tread of 13 ft. and consists of two four-wheeled chassis, one on each side
under the lower wing at the inner interplane struts. The rear wheels on each chassis
support the airplane while the front wheels which project outward and upward are
used to assist in landing.
The modified airplane has the following characteristics:
Span ... ... ....................... ............................................. .. 37'
Length .. .............. ..... , .... ............... .......... ..... ...... ... ....... 30' 4"
Height ............. ........................... ..... ...... ... .................. 10' 9"
Wing area ........ ... ... ....... .................. ............. ... ......... .420 sq.ft.
Weight empty ................. .............. ... .......... ......... ..... 1727 lb.
Weight loaded .... .. .............. ...................... ............... .. 2420 lb.
Useful load ... ....................... ........... .. .. .... ..... ..... .... 693 lb.
33
Foreign Development-France
Hanriot HD-14 E (LeRhone 80 h.p. Engine).
This model is a two-seater biplane with single cockpit and a four-wheeled landing
gear having a 15-foot tread.
Characteristics :
Span .......... ......... .... ................ .............. ...... ... ..... ....... .. 34'
Length ..... ...... ...................... ..................... .................. 26' l"
Wing area .. ............ ............. .... .......................... ....... 371 sq.ft.
Weight empty .............. ....... .... ... , ............................ 1051 lb.
Useful load ....... ......................... ............ ......... .......... 559 lb.
Qualities: Good stability, easy communication, easy to fly. Developed struc­tural
weakness in certain parts vital for training purposes.
Morane AR E (LeRhone 80 h.p. Engine).
The airplane is a two-seater monoplane of the parasol type having the following
characteristics:
Span ---·····--··--·---·-·--··-------·-----------------------·--- -·- --·-·------·--42' l"
Length ······· ··--·--···-··-··--·-·---··-·----·--··-···-······ ··-· ·-·-·-···-·· ·22' 2"
Height -········--·--· ----·-·-------·---··-------··-· ···--··-· ·-·-··-··--· ·-···11' 1"
Wing area -······ ·'· ·-·············-··-··· ···--·-· -·· ······ ··· ···-······-·· ·215.28 sq.ft.
Weight empty -···--·······--·---·----··-·····-·· ···-······--····-··-···836 lb.
Useful load --··-····-··-··-·· ·---·--···-·· ·--··-·····---··---·-····-··-···352 lb.
Speed (estimated) ·-····-·······-··· ······-···· ········· ··-·· ·-·······83.7 m.p.h.
Qualities: Excellent stability, good visibility and easy communication; difficult
to take-off or land, and controls too sensitive for beginners.
S.P.A.D. 42 ET-2 (Hispano-Suiza 180 h.p. Engine).
The machine is a two-seater, dual control, biplane having a cellule of the Herbe­mont
type. The fuselage is similar to the S.P.A.D. VII and · permits the utilization of
spare parts such as fittings, etc., of the latter model.
Characteristics :
Span -···-······ ···· ········ ···· ···· ······ ···--·· ··· ···-··---·· ··· ····· ···· ...... 28' 4"
Wing area ............. ...... ... .......... ... . ...... .. .... ........ \. .... .. 247.57 sq.ft.
Weight empty ··--·-··--···-·--····---- ··--····----··-·--···-···-·-..... 1210 lb.
Weight loaded ······ ·--············--············ ······-· ·······--·-······1903 lb.
Useful load ·· ···· ···----· ·-·- ---· --· ·······--··· ·-··-· ··--··-··-·-··· ··-·· 693 lb.
34
NEW BOOKS AND DOCUMENTS
BOOKS AND DOCUMENTS ON AERONA UTIC;\.L DEVELOPMENT AND ENGINEERING
IN THE UNITED STATES AND OTHER COUNTRIES ADDED TO REFERENCE FILES OF THE
ENGINEERING DIVISION, AIR SERVICE.
AERONAUTICS
Domestic and Foreign.
Aviation and Insurance; by R. H. :Mayo. From Premier A00.4/ 4
Congre's International de la Navigation Aerienne. Nov. 1921. Vol. 1.
National Advisory Committee for Aeronautics. May 1922. 12p.
Answer to Engineering Division questionnaire on European Cll/ 7
developments; by Maj. B. D. Foulois. M.A. Germany. Feb. 6, 1922.
Project approved by the council of ambassadors for the pur- A00/5
pose of maintaining an aeronautical supervision in Germany after the
inter-allied aviation control commission ceases to function. M. I. D.
2574-397-3. M. A. ·France. 5331-W. Mar. 24, 1922. 2p.
Report on the sixteenth m,eeting of the associate air research C34.9/ 7
committee held at Ottawa; by E. W. Stedman. Aid Board. Mar. 11,
1922. lp.
Situation of German patents in England; by Kurt Eppinger I; D00.18/ 11
tr. from Zeitschrift fur Flugtechnik und Motorschiffahrt. Dec. 15,
1921. 2p. ,
Maj. Benedict's letter to Col. Bane, telling of his first I AOO / 17
visit to the Royal Aircraft Establishment. Apr. 22, 1922. 6p.
Organization of the Dutch Air Service. M. A. The Hague.
Dec. 7, 1921. 2p.
Information furnished by Technical Section, French Air Ser­vice,
on various technical questions, in answer to the Engineering
Division questionnaire. France 5423-W . . Apr. 13, 1922. 24p.
The Rhone soaring flight competition for 1921; by Werner von
Langsdorff; tr. from Zeitschrift fur Flugtechnik und Motorluft­schiffahrt.
Sept. 30, 1921. 8p.
Some remarks regarding the Rhone, 1921, prize competition
for soaring flight; by William Hoff. Tr. from Zeitschrift fur Flug­technik
und Motorluftschiffahrt. July 30, 1921.
35
C00/ 73
Cll/ 6
D52.03/34
C71.6/ 31
New Books and Documents
The twenty-one minute soaring flight on the Neidelstein, Sept.
13, 1921; by W. Messerschmitt. tr. from Zeitschrift fur Flugtechnik
und Motorluftschiffahrt. Oct. 31, 1921. 2p.
The soaring airplane of the adademic flier group of the tech­nical
high school, Hannover; by W. Blume. tr. from Zeitschrift fur
Flugtechnik und Motorluftschiffahrt. Nov. 15, 1921. 5p.
Discussion of Roff's lecture at the 7th meeting of the "WGL"
Munich, on soaring flight; by W. Klemperer. tr. from Zeitschrift fur
Flugtechnik und Motorluftschiffahrt. Dec. 15, 1921. 5p.
Some remarks on the method of soaring flight; by Ahlborn;
tr. from Zeitschrift fur Flugtechnik und Motorluftschiffahrt. Dec.
15, 1921. 5p.
Some remarks on soaring flight; by L. Prandtl; tr. from Flug­technik
und Motorluftschiffahrt. July 30, 1921. . 5p.
Regarding the glide figure in soaring flight; by W. Klemperer;
tr. from Zeitschrift und Motorluftschiffahrt. Oct. 31, 1921. lp.
Techn.ical reports published by the Italian Army Air Service
on aeronautical development ·in various countries. In Italian with
translation. M. I. D. 2086-226/ 12. Italy 6354 on 11789. Dec. 1921.
39p. illus. charts.
Answer to aviation questionnaire, 257 4-339 M. I. 2, on a 2ro­nautics
in Poland; by Maj. E . E. Farman. M. I. D. 2574-339.16.
Poland 1718. Dec. 6, 1921. 3p.
Chart showing the organization of the War Department. n.d.
Outline chart of functions of proposed Bureau of Civil Aero­nautics,
Dept. of Commerce. SP-pt. 20, 1921.
Air Service activities of the United States army, giving station
reports and Air Service strength of commissioned regular army and
reserve corps. Feb. 1922.
Index to U. S. Army Air Service Information Circulars
(aviation) No. 101-200, Vol. 2. Feb. 15, 1922. 12p.
Directory of military stations used by Air Service troops, clas­sified
according to whether they are operated by the Air Service or
not and also according to their activities. May 1, 1922.
Directory of military stations used by Air Service troops, clas­sified
according to whether they are operated by the Air Service or
not and also according to their activities. .June 1, 1922.
United States naval aviation technical pr0gress report. Navy
Dept. Vol. 1, No. 6. May 1, 1922.
Syllabus for training of naval aviators and naval aviation
pilots. Airplane. 1922. 39p.
36
D52/16
D52/ 15
C71.6/ 35
C71.6/ 34
C71.6/ 14
C71.6/ 13
D00.12/ 78
1921-No. 10-11
Al0/1
Poland
C20/ 18
A48.2/ 70
C21/ 17
1922-Feb.
Al0/ 83
Vol. 2-No. 200
(;13/ 9
May-1922
Cl3/ 9
1922-June
D00.12/ 12
1922-May
C53.22/14
New Books and Documents
Aircraft development since the armistice. Airplanes. A lec­ture
for the Air Service reserve officers; by Lt. C. N. Mpntieth. June
12, 1922. 32p.
Aircraft development since the armistice. Armament. A lec­ture
for the Air Service reserve officers; by Armament Section. June
1922. 21p.
Aircraft development since tlle armistice. Equipment. A lec­ture
or the Air Service reserve officers; prepared by Equipment Sec­tion,
McCook Field. June 10, 1922. 18p.
List of farmers' bulletins issued by the United Stl:ltes Depart­ment
of Agriculture. Dec. 31, 1921.
Monthly list of publications issued by the Department of Com­merce.
Feb. 28, 1922.
Monthly list of publications issued by the Department of Com­merce.
Apr. 29, 1922.
Monthly list of publications issued by the Department of Com­merce
May 31, 1922.
Publications of the United States Geological Survey. Dept.
of the Interior. May 1, 1922. List No. 170.
Records.
Overseas records of Air Service squadrons with official vic­tories
and casualties; compiled by Capt. Harmel and Lt. Dennison . .
Oct. 1921. lp.
Fire Prevention.
Forest fire patrol for 1921; covering general plans and organi­zation,
patrol routes, personnel, radio, equipment, ·etc. 1922. 61p.
photostats, map,
Annual report of aerial forest fire patrol of the 91st. squadron,
located in Washington and Oregon, during the season of 1921. llp.
charts, photostats.
Season report for aerial forest fire patrol, Mather Field; by
Lt. F. S. Gullot. 1921. 34p.
Forest fire patrol report for California, district 5. 1921.
26p. maps.
Prevention of fire in single-engine<l airplanes. Aeronautical
Research Committee T. 1671. D.1 special technical questions, 86,
(F. P. 90). Dec. l 921. 13p.
Preliminary reports on experiments on the ignition and ex­tinction
of burning portions of airplanes. Air Ministry. C. I. M. 747.
M. I. D. 2083-465/2. England 13759. Apr. 21, 1922. 4p.
37
C50.02/ 4
C50.02/ 5
C50.02/ 6
D00.12/ 58
Cl3/6
Feb.-1922
Cl3/ 6
Apr.-1922
C13/ 6
1922-May
A46.2/ 8
1922-May
E40/ 4
E40/ 7
E40/ 6
E40/ 3
D00.12
T.1671
D52.l/ 29
New Books and Documents
Further notes on fire prevention; experimental evidence bear­ing
on the occurence of fires in airplanes. Air Ministry. C. I. M. 1019.
Apr. 1920. 8p. drawings.
Research.
Report of work done at the Aeronautical Experimental Insti­tute.
In Italian. Series 2a-No. 1. In Italian. Feb. 15, 1922. 47p. illus.
charts, drawings.
Reports of work being done at the Experimental Institute of
Aeronautics. In Italian. Apr. 15, 1922. 107p.
Content,,; . .
1. Discussion of various testing machines.
2. Experimental hydrodynamic researches regarding the conduct of
dirigible M.; by Bertozzi Olmeda.
3. Theory of vortices in aerodynamics (continued) ; by E. Pistolesi.
Letter of J. J. Ide on aerodynamics being studied by the Aero­nautical
Research Committee, National Physical Laboratory; by J. L.
Naylor. May 4, 1922. 3p . .
Report or the year 1920, of the National Physical Laboratory,
_ 1921. 132p. drawings.
Variation of airplane performance with atmospheric conditions.
In French. Service Technique de l' Aeronautic. Bulletin Technique
No. 4. Mar. 1922. 24p. charts.
Abacus for airplane calculation; tr. Technical Data Section.
Memo. report No. 40. McCook Field. May 18, 1922. 4p. charts.
Measurements of pressure on the airplane in flight; by A.
Proell; tr. from Zeitschrift fur Flugtechnik und Motorluftschiffahrt.
June 30, 1921. 7p.
Regarding the flying and spinning curves; by L. Hoff; tr. from
from Zeitschrift fur Flugtechnik und Motorluftsc;hiffahrt. Sept.
30, 1921. 12p.
Air force and moment for Elias E. M. seaplane.
Construction Dept. Report No. 190. May '4, 1922.
charts, drawings.
Navy Yard.
photograph,
Acceleration derivatives · in the case of a body moving in an
ideal fluid; by R. Jones. Aeronautical Research Committee. Reports
and Memoranda No. 748. (Ae. 13). (T. 1574). Apr. 1921. 8p.
Decay of a simple eddy; by H. Bateman. National Advisory
Committee or Aeronautics. Report No. 144. 1922. 7p.
Researches on diagonal stability and lateral stability with
graphical methods: by A. Baumann; tr. from Zeitschrift fur Flug­technik
und Motorluftschiffahrt. July 30, 1921. 17p.
38
D52.1/ 52
D00.12/ 117
1922-2a-No. 1
D00.12/ 117
1922-2a-No. 2
D00.12/83
F32/ 13
D00.12/ 126
1922-Mar.
D00.11/ 1
Al0.2/ 61
C71.6 /32
D52.6/ l
Elias
D00.12/ 748
Al0.2/62
Al0.2/ 10
New Books and Documents
Compressed-air illness and its engineering importance, with a
report of cases at the East River tunnels; by Edward Levy. Bureau
of Mines. Technical paper No. 285. 1922. illus. charts.
Graphic comparison of screw thread pitches, showing the num­ber
of threads per inch in millimeters for both inch and millimeter
system. Bureau of Standards. Miscellaneous publications No. 49.
Apr. 18, 1922. lp. chart. ·
Notes on the design of latticed columns subject to lateral loads;
by C. J. McCarthy. National Advisory Committee for Aeronautics.
Technical Notes No. 98. May, 1922. 18p. charts, diags.
Characteristic curves for Caproni and Nieuport aerofoils.
1918. 2 charts.
Intersected aerofoil; remarks on the article of C. Lachmann;
by G. V. Nordensvan; tr. from Zeitschrift fur Flugtechnik und Motor­luftschiffahrt.
Oct. 31, 1921. 2p.
Air force and moment for Gottingen aerofoil No. 322; by F. A.
Zahm and R. M. ·Bear. Navy Yard. Construction Dept. Report No.
186. Apr. 4, 1922. 9p. chart.
Test of Gottingen No. 457; tr. Technical Data Section. Memo.
report No. 58. McCook Field. May is, 1922. 2p. chart.
Point drag and total drag of Navy struts No. 1 modified; by
A. F. Zahm and others. National Advisory Committee for Aero­nautics.
Report No. 137. 1922. 15p. charts, diags.
Air force and moment for Elias i;eefable wing.
Construction Dept. Report No. 189. Apr. 29, 1922.
graph, charts, drawings.
Navy Yard.
5p. _·- photo-
Theory of the slotted wing; by A. Betz. National Advisory ­Committee
for Aeronautics. Technical Notes No. 100. June, 1922.
13p. diags. ·
Contributions to the problem of the intersected wing; by W.
Klemperer; tr. from Zeitschrift fur Flugtechnik und Motorluftschif­fahrt.
Oct. 31, 1921. 4p.
The tail plane; by M. M. Munk. National Advisory Committee
for Aeronautics. Report No. 133. 1922. 37p.
Contents
l. The entire airplane.
2. The tail plane.
3. The tail plane of. the JN4H.
4. · The structural strength.
39
B60/4
A48.2/ 72
D52.39/ 32
])52.338/ 144
D52.338/ 141
D52.338/143
D52.338/ 59
D52.333/ 66
D52.338/ rn6
D52.338/ 146
D52.338/ 143
D52.327/ 10
New Books and Documents
AERIAL NAVIGATION
Air Traffic.
Aerial convention of Oct. 13, 1919 for regulating international
air traffic; by Capt. Roper. From Premier Congre's International
de la Navigation Aerienne. 1922. Vol. 1. National Advisory Com­mittee
for Aeronautics. May, 1922. lOp.
Air Navigation (colonies and protectorates) order in council,
1922, No. 121, regarding navigation over the colonies. 1922. 5p.
Recent achievements of airplanes show wonderful progress.
Civilian flying can be made safe by new laws. Chinese setting very
fast pace. Air mail reaches limit of operation by news. May 23, 1922.
Air traffic; by G. Sudre. tr. from'. Premier Congre's Inter­national
de la Navigation Aerienne. Nov. 1921 . Vol. 1. National
Advisory Committee for Aeronautics. May, 19.22. 8p.
Technique and economy of . air traffic with airplanes ; by E.
Offerman. Pt. II. tr: from Zeitschrift fur Flugtechnik und Motor­luftschiffahrt.
Oct. 31, 1921. 6p.
Regulation of air traffic; by Devaluez. From Premier Congre's
International de la Navigation Aerienne. Nov. 1921. Vol. 1. National
Advisory Committee for Aeronautics. May, 1922. lOp.
Proposed air traffic law for France; by Georges Rippert. From
Premier Congre's International de la Navigation Aerienne . . Nov.
1922. Vol. 1. National Advisory Committee for Aeronautics.
May, 1922. 18p.
Irresponsibility clause in air traffic contracts; by Porquet. tr.
from Premier Congre's International de la Navigation Aerienne. Nov.
1921. Vol. . 1. National Advisory Committee for Aeronautics.
Apr. 1922. 4p.
Airways and Airdromes.
Technical problems ,of commercial flying; by E. P. Warner.
National Advisory Committee for Aeronautics. May, 1922. 6p.
· .Chart showing occupation of border airdromes by squad­rons.
n.d.
Monthly report of operation and maintenance of air mail ser­vice.
United States Post Office Dept. May, 1921; June, 1921; Dec.,
1921; Jan., 1922; Feb., 1922.
Information on machine for map-making for aerial photo­graphs.
M. I. D. 10919~27/l. Italy 6367. ON 11820. Apr. 25,
1922.' lp.
40
A00.5/ 21
A00.5/1
Great Britain
Al0/ 105
A00.5/ 19
Al0.01/ 25
A00.5/ 20
A00.5/ 2
France
A00.5/ 1
France
Al0.01/ 26
C22.32/ l
El0.2/9
D62.4/ l4
New Books and Documents
Meteorology.
Meteorological advice for the air traffic; by A. Schmauss; tr.
from Zeitschrift fur Flugtechnik und Motorluftschiffahrt. Nov. 30,
1921. 3p.
Weather forecasting, with introductory note on atmospherics;
by G. S. Bliss, 3rd. Ed. Weather Bureau Bulletin No. 42. 1921.
35p. maps.
Use Qf weather reports by the D. E. L. A. G. (Zeppelin Com­pang)
previous to airship flights. M. I. 'D. 2082-337. Germany 2534.
Nov. 2, 1921. 8p.
Mean values of free air barometric and vapor pressures, tem­peratures,
and densities over the United States. Turning of winds
with altitude; by W. R. Gregg. Weather Bureau. Reprinted from
monthly weather review. Jan. 1918. 46 ;11-21. · ilp.
Influe.nce of the wind upon transportation performance; by W.
Klemperer; tr. from Zeitschrift fur Flugtechnik und Motorluftschif­fahrt.
Nov. 15, 1921. 2p.
Question of the, measurement of the vertical component of the
wind; tr. from Luftfahrt. N. A. 910/100. July, 1921. 3p.
Electric phenomena in the atmosphere; by Alphonese Breget;
tr. Technical Data Section. Memo. report No. 41. McCook Field.
May 24, 1922. 6p.
German system for condensing and coding data for aerological
observations used in aviation forecasts. N. 0. 909/100 Serial 169.
Oct. 26, 1921. 4p.
Night Flying.
Report on night flying. Use of lights as signals. M. I. D. 2083-
470. England--11. Feb. 2, 1922. 2p. .
A40/ 13
A40.0l / 6
A40/ 12
A40/ 18
A40.2/ 6
A40.2/ 7
A20/ 8
.
A40.0l/5
C71.6/ 33
AIRPLANES, SEAPLANES, AMPHIBIANS, GLIDERS, AND HELICOPTERS
Design of a commercial airplane; by Capt. G. DeHaviland.
Royal Aeronautical Society. Mar.. 30, 1922. 4p.
Instructions concerning marking of airplane parts in accord­ance
with Air Service specifications No. 24105-E. War Dept. 0. C.
A. S. Letter of instruction No. 29. May 23, 1922. lp.
Avro.
Instructions concerning lift wire fittings on the A vro 504K.
Notice to ground engineers No. 5 of the year 1922. Air Ministry.
Apr. 21, 1922. lp.
41
D52.16/ 21
D00.12/ 76
1922-No. 29
D00.12/ 95
1922-No. 5
New Books and Documents
Breguet.
Catalog giving the general characteristics of the Breguet 14.
In French. M. I. D. 2081-314. France 5447-W. Apr. 26, 1922. lOp.
illus. drawings.
Davis Douglas.
Performance of the Davis Douglas DT2 seaplane and land­piane.
May 26, 1922. 2p.
DeHaviland. . Reinforcing . of DeHaviland 4 type landing gear axles. War
Dept. Letter of instruction No. 31. .June 9, 1922. lp.
Description of DeHaviland 29; by Major Melvin Hall. M. I. D.
2083 . 420/1. England 12292. July 19, 1921. 3p.
Fokker.
Summary of official performance test of Fokker D-9. McCook
Field. June 22, 1922. lp.
Summary of official performance test of Fokker C0-4. McCook
Field. June 22, 1922. lp.
Handley Page.
Report on tests made on the Handley Page torpedo plane; by
Maj. C. C. Benedict. M. I. D. G-2. 2083-482. England 13654.
Mar. 29, 1922. 2p.
Helicopters.
Some new projects for helicopters; very brief descriptions of
the following helicopters: Damblanc . & Lacoin, Ellehammer, Crocker­Hewitt,
Berliner, Pescara, Oemmichen, Brennan, Leineweber, Passat,
La Cierva, and Denny; tr. from Zietschrift fur Flugtechnik und
Motorluftsch~ffahrt. Dec. 31, 1921. 2p.
The captive helicopter Petroczy-Karman-Zurcvec; a report and
· description of electric and gasoline driven helicopters; tr. from Zeit­schrift
fur Flugtechnik und Motorluftschiffahrt. Dec. 31, 1921. 7p.
Theoretical remarks on the problem of the helicopter; by Th.
v. Karman; tr. from Zeitschrift fur Flugtechnik und Motorluftschif­fahrt.
Dec. 31, 1921. 20p.
42
D52.1 /3
Breguet
D52.l/ 2
Davis
Douglas
D00.12/ 76
1922-No. 31
D52.l/ 2
D.H.29
D52.l/ 32
Fokker
D52.l / 41
Fokker
D52.1/67
H. Pag€:
Al0.22/ 1
Misc.
Al0.22/ 1
Petroczy
Al0.22/ 21
New Books and Documents New Books and Documents
Mars VI.
Specifications of Mars 6 high speed fighting scout with 300 h.p.
Siddeley Jaguar engine. The Gloucestershire Aircraft Co., Ltd. n.d.
4p. photostated drawings.
Martin Bomber.
Instructions concerning changes to be made on the Lunken­heimer
radiator relief valves on the Martin MB2. War Dept. 0. C.
A. -S. Letter of instruction No. 23. May 11, 1922. lp. drawing.
Penaud & Gauchot.
Drawings-of Penaud & Gauchot. Feb. 1876.
Remington Burnelli.
Photographs of the Remington Burnelli airplane. n.d.
S. V. Airplane.
Air force and moments for S. V. monoplane. Navy Yard. Con­struction
Dept. Report No. 188. Apr. 24, 1922. 17p. charts, drawings.
Vought VE-7.
Change No. 81 to be made on model VE-7 elevator control leads.
Navy Dept. Bureau of Aeronautics. Technical Order No. 15. May
15, 1922. 2p.
AIRSHIPS AND BALLOONS
General.
The stability of airships; by R. Jones and D. H. Williams.
Aeronautical Research Committee. Reports and Memoranda No. 751.
(Ae 15). T. 1576. June, 1921. 19p.
Giant dirigibles for transportation; tr. Technical Data Section
Memo. report No. 43. McCook Field. June 3, 1922. llp.
Roma.
The Roma; historical sketch and description. Lighter-than­air
Section. McCook Field. Apr. 27, 1922. 30p. photographs.
43
D52.1; 5
Mars
D00.12/ 76
1922
No. 23
D52.l/ l
Penaud &
Gauchot
:052.1/ 1
Remington
Burnelli
D52.1/1
S. V.
D52.l/ 18
Vought
D00.12/ 751
R. &M.
D52.7; 4
Misc.
D52.7/ 4
Roma
New Books and Documents
Description of the new Italian type dirigible and notes on
lighter-than-air matters. M. I. D. 2086-282. Italy 6341. ON 11767.
Apr. 17, 1922. 8p. photostated drawings.
Method for determining range from balloons; tr. from the
German M. I. D. 2571-325. 1917. 18p.
Final trial of type · F kite balloon. Bureau of Aeronautics.
Nov. 17-Dec. 2, 1921. 5p. photographs.
ARMAMENT
Powder for small arms for use of aviation. M. I. D. 2265-C-13.
France 5324-W. Mar. 22, 1922. lp.
ELECTRICAL
Manual for Exide batteries in starting, lighting and ignition
service on passenger automobiles, power-boats, motorcycles, motor
trucks, and tractors. The Electric Storage Battery Co. May, 1921.
60p . . illus. charts, diags.
Electromotive force of cells at low temperature; by G. W.
Vinal and F. W. Altrup. Bureau of Standards. Scientific papers No.
434. Apr. 17, 1922. 8p. charts.
The field radiated from two horizontal coils; by Gregory Breit.
Bureau of Standards. Scientific Papers No. 431. Mar. 10, 1922.
18p. charts.
Sparking voltage of spark plugs; by F. B. Silsbee. Project P5.
Bureau of Standards. 4lp. charts.
Notes on the effect of electrode temperature on the sparking
voltage of short spark gaps. , n.d. 18p. charts, diags.
EQUIPMENT
Safety llelts.
Inspection of safety belts to rletermine condit10n for service.
War Dept. 0. C. A. S. Letter of Instruction No. 25. May 15, 1!)22. 4p.
Hangar.
Photostated drawings of 1000'xl50' dean space dirigible han­gar
beini erected at Orly, France. n.d.
Straight-Side Wheel.
Investigation of 28x4 straight side w~eel which failed on the
Dayton-Wright TA-3 airplane. Material Section. McCook Field.
May 31, 1922. 2p. photograph.
44
D52.7/ 1
N
Dl3.3/ 18
Sextant
D52.8/ l
F
D71.12/ 2
D13.43/ 3
D13.43/ 6
D13.41/ 147
D52.413/ 266
D52.413/ 267
D00.12/ 76
1922-No. 25
F34/ 34
D52.46/ 20
New Books and Documents
Wings.
Inspection and storage of wings. War Dept. 0. C. A. S. Letter
of Instruction No., 24 (Supersedes Letter of Instruction No. 10, May
4, 1921). May 12, 1922. 2p.
FUELS
Production of gasoline by cracking heavier oils; by E. W. Dean
and W. A. Jacobs. Bureau of Mines. Technical Paper No. 258. 1922.
56p. charts.
INSTRUMENTS
General.
General classification of instruments and problems including
bibliography; by M. D. Hersey. Aeronautics Instruments Section No.
1. National Advisory Committee for Aeronautics. Report No. 125.
1922. 22p.
New developments on airplane instruments; a description of
instruments being developed by the Bamberg Goerz and Klemperer
companies; tr. Technical Data Section Memo. Report No. 39.
McCook Field. May 18, 1922. 6p. photostated drawings.
Heylandt Air Compressor.
Report on Heylandt air compressor; tr. Technical Data Section
Memo. Report No. 37. McCook Field. May 12, 1922. 13p. photo­stated
drawings.
Adlershof Test Stand.
Description of the Adlershof altitude testing stand; by K. F.
Naegele; tr. from Zeitschrift fur Flugtechnik und Motorluftschif­fahrt.
May 17, 1921. 5p.
Aveline Stablizer.
The Aveline stabilizer for all types of aircraft. n.d. 6p. illus.
Geoscope.
Description, use and mounting of the geoscope. Dec. 22, 1921.
5p. photostated drawing.
45
D00.12/ 76
1922-No. 24
Dll.31/ 42
D13.3/3
D13.3/ 54
Misc.
Dl2/4
F32/ 12
Dl3.3/ 15
Stabilizer
D13.3/1
Geoscope
New Books and Documents
Ground Speed Indicator.
Description of ground speed indicator; by A. E. G. Post
Uiteweer. n.d. 4p. diags.
Oscilloscope.
Articles on the oscilloscope, an invention which enables one to
watch at leisure the details of action of high speed machinery. 1922.
llp. photostats.
Oxygen Apparatus.
Oxygen instruments; by F. L. Hunt. Aeronautic Instruments
Section No. 6. National Advisory Committee Report No. 1'30. 1922.
23p. illus. drawings, charts.
Description of German liquid oxygen apparatus; , by Maj. B.
D. Foulois. M. I. D. C-2. 2307-B-46/ l. France D-3000. Mar. 3,
1922. 4p.
Protractor.
The vector ruling protractor; by A. F. Zahm. Navy Yard Con­struction
Dept. Report No. 187. Apr. 12, 1922. 4p. photographs,
diag .
. Dresler Steering Gauge.
Description of Drexler aircraft steering gauge. n.d. 4p. illus.
Sylphon Diaphragms.
I
Sylphon diaphragms; a method for predicting their perfor-mance
for purposes of instrument design; by H. N. Eaton anJ} G. H.
Keulegan. National Advisory Committee for Aeronautics. Technical
Notes No. 90. May 1922. 14p. diags., charts.
Thermometers.
New calorimetric resistance thermometers; by H. C. Dickinson
and E. F. Mueller. Bureau of Standards. Reprint No. 200 from Bul­letin,
Vol. 9. Jan. 1, 1913. lOp. illus. diags.
Viscometer.
Redwood vis~ometer; by W. ·H. Herchel. Bureau of Standards.
Technological Papers No. 210. Apr. 10, 1922. 20p. charts.
46
D13.3/ 5
Ground Speed
Indicator
D13.3/ l
Oscilloscope
Dll.331/ 18
Dll.331/42
D13.3/ 2
Protractor
Dl3.3/ l
Steering
Gauge
Dl3.3; 1
Sylphon
D13.3/17
Thermometer
D13.3/ 1
Viscosimeter
•
New Books and Documents
Voltmeter.
Calibration of Wilson-Maeule,n millivoltmeter and pyod couple,
submitted by Supercharger Branch, Material &ction. McCook Field.
June 9. 1922. 2p.
MATERIALS
On the testing of material in airplane works; , by K. Balabon;
tr. from Zeitschrift fur Flugtechnik und Motorluftschiffahrt. Aug.
15, 1921. 8p.
Fabric.
Deterioration of airplane fabric covering with ag.e; by Wendt;
tr. from Zeitschrift fur Flugtechnik und Motorluftschiffahrt. Nov.
30 1921. 3p.
Instructions concerning use of thread for sewing airplane fabric
and specification for linen thread Navy Dept. BuI1eau of Aero­nautics.
Aircraft Technical Order No. 10. May 30, 1922. 3p.
Metals
Report on aluminum alloy bearing blocks, manufactured by
Aluminum Manufacturers, Inc. Material Section, McCook Field. May
11, 1922. 2p. photographs.
PHOTOGRAPHY
Airplane photography; its present day status and future de­velopment;
by Erich Ewald; tr. from Zejtschrift fur Flugtechnik und
Motorluftschiffahrt. May 17, 1921. 5p.
Report on work being . done at the Bureau of Standards on
ammonia tables, sensitometry of photographic emulsions and a survey
of the characteristics of plates and films of American manufacturers,
etc. June 8, 1922. 15p.
POWER PLANTS
Metallurgical problem of the aviation engine. 'In French. Ser­vice
Technique de l' Aeronautique. Bulletin Technique No. 5. April,
1922. 17p.
Comparing maximum pressures m internal combustion en­gines;
by S. W. Sparrow and S. M. Lee. National Advisory Com­mittee
for Aeronautics. Technical Note No. 101. June, 1922. 3p. diags.
Description of the power plant laboratory, Engineering Divi­sion,
McCook Field; by Robert Insley. Power Plant Section. McCook
Field. May 19, 1922. 6p. photographs.
47
D13.3/ l
Millivoltmeter
D13.6/ 50
D24.31/85
Dl0/ 69
D52.419/ 80
A30.2/ 25
D00.12
T. B. 62
D00.12/126
1922-A~ril
D52.41 / !:16
F35/ 15
~ew Books and Documents
Ansaldo "12".
Dynamometer test of Ansaldo "12" airship engine, type 4E-28,
No. 1017; by Marsden Ware. Langley Field. Oct. 17, 1921. 5p. charts.
French Hispano-Suiza.
General characteristics of French 300 h.p. Hispano-Suiza.
n.d. 2p.
Liberty "6".
Report on defective Liberty "6"
Power Plant Section. Material Section.
1922. 3p. photographs.
Siddeley "Jaguar".
cranksh.aft, submitted by
McCook Field. May 18,
Description and letter concerning purchase of Siddeley Jaguar
engine. M. I. D. 2083-333/8. England 13673. Apr. 14, 1922. 11p.
blueprints.
Ignition Systems.
List of standard spark plugs in order of choice for the types
of engines used in the Air Service. War Dept. 0. C. A. S. Letter of
Instruction No 28. May 22, 1922. lp.
PROPELLERS
List of propellers regarded as most suitable for the variom;
airplanes and engines. War Dept. 0. C. A. S. Letter of Instruction
No. 27. May 18. 1922. 2p.
Notes on propeller design IV. General proceeding in design;
by M. M. Munk. National Advisory Committee for Aeronautics.
Technical Notes No. 96. May, 1922. 9p. diag.
Graphic computation of propeller performances after model
tests; by Adolph Rohrbach;· tr. Technical Data Section Memo. Report
No. 42. June 2, 1922. 6p. charts.
On special construction of propellers; by Jacob Haw; tr. from
Flμgtechnik und Motorluftschiffahrt. Aug. 15, 1921. 6p.
Re-balancing of propellers after re-tipping or re-painting. No­tice
to ground engineers No. 6 of the year 1922. Air Ministry. May
15, 1922. lp.
Instructions concerning inspection of stored propellers. War
Dept. 0. C. A. S. Letter of Instruction No. 26. May 16, 1922. lp.
48
D52.41/ 4
D52.41/ 83
H. Suiza
D52.41/ 121
Liberty
D52.,41/13
Siddeley
D00.12/ 76
1922-No. 28
D00.12/ 76
1922-No. 27
D52.43/ 292
D52.43/ 44
D52.43/ 290
D00.12/95
1922-No. 6
D00.12/ 76
1922-No. 26
I
\
New Books and Documents
Amendment to Letter of Instrq.ction No. 20, series 1922, re­garding
propellers used on Curtiss JN4H and JN6H. War Dept. 0. C.
A. S. Letter of Instruction No. 30. May 27, 1922. lp.
Thrustmeter test on propeller made from drawing X-7039. Pro­peller
research report No. 4. McCook Field. Oct. 1, 1920. 24p. charts.
Technical remarks and advertising pamphlets on the Haw Air­screw.
n.d. 14p. illus.
RADIO
List of new commercial and government land and ship radio
stations, corrections, etc. Apr. 1, 1922. 26p.
Supplement No. 7 for international list of radio telegraph sta­tions
and their call signals. Mar. 15, 1922.
R,eport on work being done at the Bureau of Standards, cover­ing
meetings of Amerian Physical Society and Association of Scientific
Apparatus Makers, Department of Commerce Conference on Radio
Telephony, publications on the simple radio reoeiving sets, etc. May
10, 1922. 13p.
Report on transmitting and receiving apparatus, radio compass,
coastal radio stations. Bureau of Engineering. Navy Dept. monthly
radio reports Mar. 1, 1922.
Report on transmitting and receiving apparatus, radio com­pass,
coastal radio stations. · Bureau of Engineering. Navy Dept.
monthly radio reports. April 1, 1922.
Construction and operation of a simple home-made radio receiv­ing
outfit. Bureau of Standards. Circular No. 120. Apr. 24, 1922.
16p. diags.
49
D00.12/ 76
1922-No. 30
D52.43/ 291
D52.43/6
D13.41/127
No. 60
Cll.2/ 12
D00.12/ 61
T. B.
D00;12/ 94
1922·
Mar.
D00.12/ 94
1922-Apr.
D13.41/ 49
RECENT ACCESSIONS TO THE ENGINEERING DIVISION LIBRARY
Author Title
American Society of
Mechanical Engineers Safety code for elevators
Bauer Helmholtzche wirbelttheorie
Bayern flugmotor, type BMW-3a
Bond & Sherrill America in the great war
Breget Ou en est la meteorologie
Card Air Navigation
Crosara Crorrologie aeronautica
Dale Map reading
Dorner & Isendahl Flugmotoren
Fries & West . Chemical warfare
Gardner Paint technology & tests
Griffiths Engineering instruments & meters
Harrison Wireless telephone construction
Heine Safety Boiler Co. Marine boiler logic
Kessner
Martin
Ausnutzung und veredlung Deutscher
rohstoffe
Electrical transmission of photographs
50
Classification
621.877
Am3
539.1
B32
629.183
B34
940.9
B64
551.5
B45
629.145
C17
629.13
C88
526.8
D15
629.183
D73
538.~
F'91
667.6
617pai
620.7
G87
621.384
H24
621.1845
H36
670
K,18
621.3826
M36
., (
Author
Martinot-Lagarde
Monckton
' Muller-Breslau
Porter
Preston
Robinson
Rouch
Schmid, Hugh S. de
Schwengler
Smith
U. S. Ordnance Dept.
Van Gries
Title
Nouveaux moteurs d'aviation
Hydrogen manual, pt. 1 & 2
Graphische statik der baukonstruktionen
Aerial observation
Theory of heat
Manual on radio telegraphy & telephony
Manual practique de meterologie
Feldspar in Canada
Statik im flugzenbau
14,000 miles thru the air
Manufacture of optical glass
Flugzengstatik
51
Classification
629.183
M36
665.8
M74
620.1
M91
629.13
P83
536.1
P92
621.384
R56
551.5
R75
553.66
Sc3
629.18
Sc9
629.13
Sm6f
666.1
Un3
629.18
V26 .
•
•