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3 1706 025 85051 7
File D 52.1 / Boeing/ 7
AIR SERVICE IN
<AVIATION>
PUBLISHED BY THE CHIEF OF AIR SERVICE, WASHINGTON, D. C.
Vol. VI April 1 . 1925 No. 502
OFFICIAL PERFORMANCE TEST
OF BOEING PW-9 EQUIPPED WITH CURTISS D-12
LOW COMPRESSION ENGINE
( FL YING SECTION REPORT)
Prepared by
Engineering Division, Air Service
McCook Field, Dayton, Ohio
November 29, 1925
WASHINGTON
GOVERNMENT PRINTING OFFICE
1925
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t-\~'t 17 10'3
Non-oepo\tmv.
"ubufO Un\\lers\W
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.
(JI)
_;• • : ~ ~. I r ~ ,.
OFFICIAL PERFORMANCE TEST OF BOEING PW~9 EQUIPPED
WITH CURTISS 0 - 12 LOW COMPRESSION ENGINE
OFFICIAL PERFORMANCE TEST- SUMMARY OF
RESULTS
NOVEMBER 29, 1924.
Airplane: Boeing PW- 9.
Ty pe : Pursuit.
A. S. No.: 23- 1218; P- 356.
Pilot: Lieutenant Ba rksdale.
Engine: Curtiss low compression.
T ype: D- 12.
A. S. No. : 23- 173; manufacturer 's No. 186, P ower
Plant Laboratory.
Rated horsepower: 411.5 at 2,170 revolu t ions per
minu te.
Propeller man ufacturer: Curtiss.
Drawing or inspection No.: X- 29048-A.
Diameter: 7 feet 10 inches.
Pitch: 7.1 feet.
Designed NVD .832.
Zero thrust pitch: 9.63 feet.
WEIGHTS
Weight empty with water_ __ _______ ____ __ _
Armament_ __ ____ _____________________ __ _
Equipment_ ___ _________________________ _
Crew ___ __ __________________________ ___ _
Gasoline (75 gallons) _____________________ _
Oil (7.5 gallons) ___________________ ____ __ _
Pounds
2, 05?
215
61. 5
180
450
56. 2
Total weight loaded _____ . ________ __ 3, 014. 7
Wing area (including aileron s) : 267.76 square feet.
Wing loading: 11.26 pounds per square foot.
Rated power loading: 7.32 pounds per horsepower.
Ground revolut ions per minute: 1,980.
'Vas armament in place d uring all tests? Ballast
substituted for guns a nd ammunition.
Data converted to standard
I
(a) Speed I (b) Climb Level
ty It. d Rate,
Densi- Tp:~: Standar_d --i--. I
sta111d- ture, a~ itu e Time feet
ard stan d- 1n feet M. P. R. P. in min- per _ R. P. M. P.
arcl H . I M. utes min- M. H.
utes
--------- --- - --------
oc.
l. 000 + 15 0 98 2, 025 0 I, 545 2, 195 164. 0
. 863 + 4. 5 5 000 102. 5 2, 005 3. 6 I, 190 2, 165 159. 8
. 824 +I. 5 6: 500 1.03. 5 1, 995 5. 0 I, 085 2, 155 158. 0
. i3i -4. 5 IO, 000 lOo. 5 1, 970 8. 6 840 2, 120 154. 0
.624 -12 1.\,000 108. 0 1,915 16.5 480 2,035 144.5
. 524 -18. 5 20, 000 109. 4 1, 835 34. 5 125 1, 880 12i. 5
---~517· ·:..:20--- , ~g; ~ · 109~5- ·1;825- --3;-_-o- --- 100
0
-- - l·,-~9-,6-55· 1-- 112150- ~o
-- ------ ____ _ '21, i50 110 1, 795 - ------
t Service ceiling.
35468-25t
' Absolute cei ling.
Landing speed: Approximately 64 miles per hour.
Minimum speed at sea le vel: Approximately G5
miles per hour.
Maximum path angle of climb: ---.
Endurance full throttle at 10,000 feet (including
climb): Approximately 2 hours 45 minutes.
Fuel consumption: 56 pounds per brake horsepower
per hour.
Gas: 450 pounds.
Oil for 6.)4 hours.
No fuel economy tests run on t hi s a irpla ne.
DISTRIBUTION OF WEIGHTS
(By po,rndsl
Weight empty (with water) _______________ _
Arma:ment and equip1nent (armament, 215;
equipment, 61.5) __ _________________ __ _ Crew ______________ _________________ ___ _
Gasoline (75 gallons) _________ ____ ______ __ _
Oil (772 gallons) ____ _________________ ____ _
Weight loaded __ ----- ----- - ------- ----- -Weight
on front wheels (tail skid on ground) __
Weight on tail skid (tail skid on ground) __ ___ _
Weight on front wheels (fl; ing position) ___ __ _
Weight on tail skid (flying position) ___ ______ _
2, 052
276. 5
180
450
56. '.l
3, 014. 7
2, 595
419
2, 722
292. 5
Center of gravity (distance from wheels in fl.ving
position) , 19.5 inches a ft .
33 per cent mean average chord.
6.2 inches above propeller axis at hub.
17 inches aft of leading edge at root.
Provisions for special equipment not carried during
test.
DESCRIPTION OF AIRPLANE
DIMENSIONS
Overall span: 32 feet 1 inch .
Overall length: 22 feet 10.)4 in ches.
Overall height: 8 feet 9 inches.
In fl~· in g position: 5 feet 3 inches.
At rest: 6 feet.
AIRPLANES
Wing curve: Gottingen, 436.
Sweepback: T a pered.
Dihedral , degrees : None.
Stagger: 14° 11 inches.
T otal area, including ailerons: 267.76 square feet.
Gap: Mean gap, 52 inches ; gap chord ratio, 0.87.
UPPER PLANE
(Includ ing renter section)
Span: 32 feet 1 inch .
Chord : 71.5 inches to 30 inches.
Area, with ailerons: 165.2 square feet.
Incide nce, degrees: Root, 0° ; right har:id, 30 feet;
left hand, 10 feet.
(1)
..• ,.,..
.. .
LOWER PLANE
Span: 22 feet 6 inches.
Chord: 58 inches to 0 inch.
Area: 81.5 square feet.
Incidence, degrees: Root, 0°; tip, +021; dihedral,
+ 1° 231. Lower surface.
AILERONS OR FLAPS
Number: 2.
Arrangement: Trailing edge upper wing.
Upper length: 8 feet 10 inches.
Upper chord: 8.5 inches to 12 inches.
Upper area: 14.76 square feet.
Lower length: None.
Lower chord: N()ne.
Lower area: None.
Total area: 14.76 square feet.
2
Distance from center of ailerons to longitudinal axis
of airplane: 11 feet 772 inches.
CENTER SECTION
· Area: None.
STABILIZER
Area: 20 square feet.
Setting: Adjustable, ·+3° to -3°.
Chord: 30 inches.
ELEVATOR
Area: 9.73 square feet.
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: 2872 inches wide
by 5172 inches deep.
Distance of maximum section from leading edge,
lower plane: 12 inches aft.
LANDING GEAR
Number of wheels: 2.
Tread: 5 feet 572 inches.
Shock-absorbing system: Elastic chord.
Braking device: Tail skid.
Wheels ahead of center of gravity: 19.5 inches.
Area: 6.3 square feet; chord, 18 inches.
Landing angle: 13~ 0 •
Area: 3.88 square feet.
DESCRIPTION OF POWER PLANT
"/<Make: Curtiss.
'Factory No.: 186.
A. S. No.: 23-173.
ENGINE
Type: D-12 low compression.
Number in plane: I.
Location: Nose of fuselage.
Rated horsepower: 411.5.
Rated revolutions per minute : 2,170.
Bore: 472 inches.
Stroke: 6 inches ..
Compression ratio: 5.3:1.
Weight dry: 671 pounds.
Gas consumption: 0.53 pounds per brake horsepower
per hour.
Oil consumption: 0.015 pounds per brake horsepower
per hour.
Weight of water in engine: 44 pounds.
Remarks: Data as furnished by Curtiss Co.
IGNITION
Battery or magneto: Magneto.
Make: Splitdorf H. T.
Type: SS- 12.
Number: 2.
Plugs, make: A. C.
Make: Stromberg.
Type: NA-Y5 .
Number: 2 .
CARBURETORS
Main metering nozzle: No. 45 D. S.
Choke : 1 ft inches.
Main discharge nozzle bleeder: No. 49 D. S.
Fixed idle bleed: No. 40 D. S.
Make: Boeing.
Type: Tunnel.
RADIATORS
Number : One, core A. S. standard 9 inch.
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, gallons per minute at 25 pounds gauge
pressure : 0.66.
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
streamlined.
LUBRICATION
Capacity of oil tank: 10.5 gallons.
Dimensions of oil tank:
Depth: 5% inches. 11f
Oil used (brand): 2-23-E.
Oil pressure: 100 pounds to 120 pounds.
Oil temperature: 140° to 160° F. inlet.
Type pump: Gear.
Wet or dry sump: Dry.
Description of lubrfoation system: Full pressure feed
to all bearings.
FUEL SYSTEM
Number of tanks: 2.
Location: 1 gravity in upper wing (center main tank
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: Standard quadrant with push and pull
rods, bell crank, and jackshaft.
PROPELLER
Make: Engineering Division.
Number of blades: 2.
Diameter: 7 feet 10 inches.
Pitch: 7 .1 feet.
Clearance: 16 inches.
Manufacturer's No.: X-29048-A.
A. S. No.: 24--11.
Remarks: Curtiss speed propeller.
PILOT'S OBSERVATION
FLYING QUALITIES
3
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 directionally.
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,
First Lieutenant, Air Service, Test Pilot.
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