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. CONFIDENTIAL
File D 52.1 /Boeing/5
<AVIATION)
PUBLISHED BY THE CHIEF OF AIR SERVICE, WASHINGTON, D. C.
Vol. V October 1 , 1924 No. 479
OFFICIAL PERFORMANCE TEST
OF BOEING PURSUIT PW-9 EQUIPPED WITH
CURTISS D-12 HIGH COMPRESSION ENGINE
( FL YING .S.ECTION REPORT )
Prepared by Engineering Division, Air Service
McCook Field, Dayton, Ohio
· July 3, 1924
WASHINGTON
GOVERNMENT PRINTING OFFICE
1924
Ralph Brown Dnn. : ,,. ,
LIBRARY -· .•
MAY 16 2013
Non·Depoitory
Auburn University
CERTIFICATE: By direction of the Secretary of War, the matter contained herein is published as administrative
information and is required for the proper transaction of the public business.
(II)
/' OFFICIAL PERFORMANCE TEST
EQUIPPED WITH CURTISS D
ENGINE
URSUIT PW-9
COMPRESSION
SUMMARY OF RESULTS
JUNE 30, 1924.
Airplane: Boeing PW- 9.
Type: Pursuit.
A. S. No. 23-1218, P-356.
Pilot Lieutenant Barksdale.
Engine: Curtiss.
Type: D-12, high compression.
A. S. No., 23-153; mfg. No. 124.
Rated horsepower: 448 at 2,240 revolutions per
minute.
Power plant: Eng. Liaison Branch.
Propeller manufacturer: 23-2495.
Drawing or inspection No. : Drawing, X47511;
inspection, 06257.
Diameter: 8 feet 2 inches.
Pitch: 6.84 inches.
Designed NVD 0.816.
v Zero thrust pitch: ND 9.95 feet.
WEIGHTS
Weight empty (with water) __ __ ___ ____ ___ _ Armament ___ c _ ____ ____ ___ ___ _ ___ __ _ _ ___ _
Equipment ____ _______ ____ ___ __ ____ ____ _ Crew ___ __ ___ _____ ___ ___ _____ ___ ____ ___ _
Gasoline (75 gallons) __ _____ ____ ____ ______ _
Oil (7.5 gallons) ____ _______ _____ _____ __ __ _
Pounds
2, 052
215
61. 5
180
450
56. 2
Total weight, loaded __ ____ ____ ____ __ 3, 014. 7
Wing area (including ailerons) and landing gear:
267.76 square feet.
Wing loading: 11.76 pounds per square foot.
Rated power loading: 7.2 pounds per horsepower.
Ground revolutions per minute: 1,970.
Was armament in place during all tests? No.
Compensated by ballast:
Re la-tive
den-sity
--
0. 964
. 830
. 791
. 706
. 595
.509
. 496
30 pounds for 30-caliber gun.
52 pounds for 50-caliber gun.
39 pounds for ammunition, 30-caliber gun.
54 pounds for ammunition, 50-caliber gun.
17 5 pounds ballast.
Stand-
(a) Speed (b) Climb
Temp. ard Time Rate
0 c. altitude M. R. in ft. R. IM. in feet p . h . p.m. min. min. p.m. p. h.
- - --- --- --------- - -
+31 0 163. 0 2, 240 0 1, 445 2,065 103. 7
+17 5,000 160. 4 2,210 3. 9 I, 125 2, 02.1 104. 8
+15 6. 500 159. 3 2, 190 5. 3 1, 028 2, 010 105. 3
+9.5 10, 000 156. 3 2, 145 9.1 675 1, 985 106. 2
+1 15, 000 150. 0 2,075 16. 9 485 1, 945 107. 5
-10. 5 20, 000 137. 0 1, 975 33. 7 165 1, 900 108. 7
21, 000
service } 131. 0 I, 945 41. 0 100 1, 800 109. 0
- 13. 5 ceiling .
22, 600
absolute } 109. 2 1, 880 ------ 0 1, 880 109. 2
ceiling.
Landing speed: 64 miles per hour.
Minimum speed at sea level : 65 miles per hour at
1,240 revolutions per minute.
Distance to take off: 410 feet.
Distance rolled on landing: 1,057 feet.
Average of three trials in wind of approximately 5
miles per hour.
Endurance full throttle at 10,000 feet (including
climb): Approximately 2 hours 35 minutes.
Fuel consumption: 0.56 pound per brake horsepower
hour at 0 altitude.
Gas: 450 pounds.
Oil for approximately 6U hours.
No fuel-economy tests run on this airplane.
DISTRIBUTION OF WEIGHTS
Weight empty (with water) ______________ _
Armament and equipment (armament, 215;
equipment, 61.5) ___ ____ ___ _____ ____ _____ __ _
Crew ___ ____ ____ __ _____ ______ ___ __ ___ __ _
Gasoline (7 5 gallons) ____ _______ ____ ___ __ _ Oil (77-:J gallons) ___ _____ ______ ________ ___ _
Pounds
2, 052
276. 5
180
450
56. 2
Weight loaded ____________ __ __ ______ 3, 014. 7
Weight on front wheels (tail skid on ground) __ 2, 595
Weight on tail skid (tail skid on ground)__ ____ 419
Weight on front wheels (flying position) __ ____ 2, 722
Weight on tail skid (flying position) ___ _______ 292. 5
Center of gravity (distance from wheels in
flying position) __________ _____ inches aft__ 19. 5
Provisions for special equipment not carried during
test.
33 per cent M. A. C.
6.2 inches above propeller axis at hub.
17 inches aft of L. E . at root.
DESCRIPTION OF AIRPLANE
DIMENSIONS
Over-all span: 32 feet 1 inch.
Over-all length: 22 feet IOU inches.
Over-all height: 8 feet 9 inches.
In flying posit ion: 5 feet 3 inches.
AI RPI, ANES
Wing curve: Gottingen 436. •
Sweep back: Taper.
Dihedral, degrees: Upper 1° lower surface.
Stagger: Degrees, 14° ; inches, 11.
Total area, including ailerons: 267.76 feet.
Gap: Mean, 52 inches; gap, chord ratio, 87.
10006-24t (1)
UPPER PLANE
(Including center section)
Span: 32 feet 1 inch.
Chord: 71.5 to 30 inches.
Area: 165.2.
Incidence, degrees: Root, 0°; right hand, 30'; left
hand, 10'.
Landing gear area: 6.3 square feet.
Chord: 18 inches.
LOWER PLANE
Span: 22 feet 6 inches.
Chord: 58 inches to 0.
Area: 81.5.
Incidence, degrees: Root, 0°; tip, +20'.
Dihedral: 1° 23' lower surface.
AILERONS OR FLAPS
Number: Two.
Arrangement: Trailing edge upper wing tips.
Upper length: 8 feet 10 inches.
Upper chord: 8.5 to 12 inches.
Upper area: 14.76 square feet.
Lower length: None.
Total area: 14.76 square feet.
Distance from center of ailerons to longitudinal
axis of airplan,e: 117 inches.
CENTER SECTION
Area: None.
STABILIZER
Area: 20 square feet.
Setting, adjustable: +3° to - 3°.
Chord: 30 inches.
ELEVATOR
Area: 11 square feet.
2
Distance from leading edge of elevator to center of
gravity of airplane: 181.5 inches.
RUDDER
Area : 5.73 square feet.
Distance from leading edge of rudder to center of
gravity of airplane: 184.5 inches.
FUSELAGE
Maximum cross-section shape: Rectangular.
Maximum cross-section area: 10.19 square feet.
Maximum cross-section dimension: 287'!! inches
wide by 517'!! inches deep.
LANDING GEAR
Number of wheels: Two.
Tread: 5 feet 57-!! inches.
Shock-absorbing system: Elastic cord.
Braking device: Tail skid.
Wheels ahead of center of gravity: 19.5 inches.
Landing angle of airplane: 13~ 0 •
FIN
Area: 3.88 square feet.
DESCRIPTION OF POWER PLANT
Make: Curtiss.
Factory No.: 124.
A. S. No. : 23- 153.
Type: D- 12.
ENGINE
Number in plane: One.
Location: Nose of fuselage.
Rated horsepower: 425.
Rated revolutions per minute: 2,000.
Bore: 4.5 inches.
Stroke: 6 inches.
Compression ratio: 5.8:1.
Weight dry: 671.
Gas consumption : 0.56.
Oil consumpti~n : 0.02 pound per horsepower hour.
Weight of water in engine: 44 pounds.
Remarks: High compression. Above data furnished
by test engineer, power plant.
IGNITION
Battery or magneto: Magneto.
Make: Splitdorf SS-12.
Number: Two.
Advance, degrees: · L. 33°, R. 38°.
Gap interrupter: 0.020.
Distributor: Jump spark.
Plugs, make: AC.
Type: Porcelain.
Gap: 0.023.
CARBURETORS
Make: Stromberg.
Type: NAY-5.
Number: Two.
Setting jet: 45 main, 29 air-bleed.
Choke: lft.
Compensator: None.
Gas drains: Direct from scoop to bottom of fuselage.
Air intake: Vertical scoop.
Mixture control: Integral.
Effect'ive to altitude: Yes.
Make: Boeing.
Type: Tunnel.
RADIATORS
Number: One core A. S. standard 9 inches.
Position: Below engine.
Frontal area: 2.64 square feet.
Depth: 9 inches.
Length: 22.5 inches.
Width: 23% inches.
Radiator surface: 235 square feet.
Temperature adjustment: Shutters.
Water capacity: 51 pounds.
Flow at 25 pounds gauge pressure: 66 gallons per
minute.
Thermometers, make: Boyce.
Weight: 107 pounds.
Type: "C."
Water capacity of whole system: 12.5 gallons.
EXHAUST PIPES
Description: Boeing special design; divided manifold;
2 each side of motor; 1 stack to 3 cylinders; stacks
stream lined.
LUBRICATION
Capacity oil tank: 10.5 gallons.
Dimensions oil tank: Irregular.
Oil used (brand): 2-23- G2.
Oil pressure: 120 pounds.
Oil temperature: 140° to 150° F.
Type pump: Integral with engine.
Wet or dry sump: Dry.
Description lubrication system: Pressure.
FUEL SYSTEM
Number of tanks: Two.
Location: One gravity in upper wing center section.
Main behind fire wall.
Capacity, main: 360 pounds.
Capacity, reserve: 90 pounds.
Gauge: Leak proof.
Description of fuel-supply system: Standard C-5
gear pump system.
ENGINE CONTROL
Description: Starnfard quadrant with push and pull
rods.
PROPELLER
Make: Eng. Div.
Number of blades: Two.
Diameter: 8 feet 2 inches.
Pitch: 6.84 feet.
Manufacturer's No.: X 47511.
A. S. No., 23-2495; inspection No., 06257.
3
Remarks: Designedl 0.816.
ND
Zero thrust pitch
9.95 feet.
PILOTS' OBSERVATION
FLYING QUALITIES
Taxi-ing- This plane taxies excellently, even in strong
wind. This is due, no doubt, to a very effective
steerable tail skid.
Take-off.-This plane takes off easily after a moderate
run and has no tendency to ground loop. Controls are
effective.
Landing.-This plane lands moderately slow and
very easily. There is no tendency to pancake or ground
loop.
Stability.-This plane is stable laterally and direct.
ionally. It is slightly unstable longitudinally, though
this is not considered to be a serious disadvantage for
a pursuit airplane. There appears to be no tendency
in this airplane to hunt at high speed or in a dive.
Maneuverability .- This plane is exceptionally maneuverable.
It loops easily, spins and rolls very rapidly,
and does all the usual maneuvers in a very satisfactory
manner. It does, however, have, to some extent, a
tendency to squash on being pulled too quickly into
a vertical turn. This is undesirable, but, considering
the wing loading and speed, it is not believed that this
fault is sufficient to disqualify in consideration of this
type. The controls are very effective and easy to
operate, though none are balanced.
VISIBILITY
The visibility is excellent for pursuit and combat
work. The blind area is relatively very small. In
landing the visibility is also very good.
MAINTENANCE
The maintenance of this plane should be easy as
the construction is very simple and accessible.
ADAPTABILITY
This plane is superior to our present pursuit plane,
the MB-3.
E. H. BARKSDALE,
Test Pilot.
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