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              Auburn University Libraries
1111111 1111111111111111111111111 1111111111111111111111111 1111111111111111111111
31706 025 85017 8
D REPOR T , SERI AL No . 2227
AIR SERVICE INFOR IRCULAR
PUBLISHED BY THE CHIEF OF AIR SERVICE, WASHINGTON, D. C.
Vol. V March 15, 1924 No. 460
PERFORMANCE TEST OF BOEING PURSUIT, TYPE I
EQUIPPED WITH CURTISS D-12 ENGINE
(PERFORMANCE TEST REPORT No. 11 3 )
Prepared by Engineering Division, Air Service
McCook Field, Dayton, Ohio
October 8, 1923
WASHINGTON
r Ralph Brown Draughon
t mfH\HY
MAY ~i 4 Z013
Non-b.epgitory
Aub,Utn University
I
GOVERNMENT PRINTING OFFICE
1924
CERTIFICATE: By direction of the Secretary of War the matter contained h erein
is published as administrative information and is required for the proper transaction
of the public business.
(n)
'/
PERFORMANCE TEST OF BOEING PURSUIT, TYPE I,
EQUIPPED WITH CURTISS 0~ 12 ENGINE.
OFFICIAL PERFORMANCE TEST- SUMMARY OF
RESULTS.
OcTOB}JR 8, 1923.
Airplane: Boeing Pursuit.
No. : (P-309) .
Type: L
Engine: Curtiss D- 12 (low compression) .
Propeller: Curtiss Climbing X-29064.
Equipped as : Pursuit.
Weight empty (including water) _____ __ ___ ____ _
Armament and equipment _ ___ _______ __ _____ _
Armament: 215 pounds.
Equipment: 55 pounds.
Crew __ ______________ _____ - __ - _____ - - - - - - - -
Gasoline: (Capacity 69 gallons, 408 pounds; bal-last
42 pounds) __________________________ _
Oil: (Capacity 6.5 gallons, 49 pounds; ballast
11 pounds ____ __________ ___ ___ ___ _____ __ _
Ponnds.
2, 011
270
180
450
60
Weight loaded __________ ___ ___ ______________ 2, 971
Weight per square foot, 11.74 pounds (253 square
feet. Total area inclusive ailerons).
Weight per horsepower, 6.76 pounds (440 horsepower
at 2,380 revolutions per minute).
(Horsepower estimated, test eng.)
Stand- Climb. Speed.
ard
taul tdie- 'l'ime . Rate, Trne Flow, I
f~~~- in min. R. p. m. f~h~.r speed. M. p. h. R.p.m. ~~~u~~r
--- ---------- --------- - -
6 500 io:ooo
15,000
20,000
25, 000
1?2 000 222; 850
3. 8
6. 7
12. 8
24. 7
34. 9
2,130
2,090
21075
2, 055
2,040
1 Serv"ice ceilin g.
2,055 84. 5 160.9 2, 380
1, 365 86.6 1.54.3 2 330
1,025 88.6 150.2 2'.295
625 94. 7 142.9 2,235
270 105. 4 132. 2 2,135
100 111. 8 124. 0 2,070
0 115. 5 115. 5 2,030
2 Absolute ceiling.
Endurance, full throttle at 10,000 (including climb):
approximately 2 hours, 50 minutes.
Minimum speed at sea-level (lowest throttle): 67
miles per hour at 1,355 revolutions per minute.
Landing speed: 64 miles per hour.
DISTRIBUTION OF WEIGHTS.
Weight empty (with water) ____ ____ ______ __ ___ _
Armament and equipment _____ ____ ___ ______ _
Armament, 215.
Equipment, 55.
Crew _______ _________________ - -- - - - - - - - - - - -
Gasoline: (Capacity 69 gallons, 408 pounds; bal-last
42 pounds) ___ _____ __ _______ _____ ____ _
Oil: (Capacity, 6.5 gallons, 49 pounds ; ballast,
11 pounds) ______ _____ __ ____ __ _____ _____ _ _
Ponnds.
2, Oll
270
180
450
60
Weight loaded ___ ____ __ ___ _______ _______ ____ 2, 971
Weight on front wheels (tail skid on ground) __ 2, 509
Weight on tail skid (tail skid on ground)____ ____ 462
Weight on front wheels (flying position) ________ 2, 681
Weight on tail skid (flying position)_ ____ ___ ____ 290
c~_nter of. ~ravity (distance from wheels in fly-mg
pos1t10n) _ _ _ ___ _ _ ___ _ _ _ __ __ _ _ _ _ _ _ __ _ 19.4
Provisions for special equipment not carried during
test.
DESCRIPTION OF AIRPLANE.
Dlil>IENSIONS.
Over-all span: 32 feet 1 inch.
Over-all length: 22 feet lOi inches.
Over-all height: 8 feet 9 inches.
In flying position: 5 feet 3 inches.
AIRPLANES.
Wing curve: Goettingen 436.
Sweepback: Taper.
Dihedral, degrees: Upper 1° lower surface.
Stagger : 14° (11 inches).
Total area, including ailerons: 253.05 square feet .
Gap: Mean- 52 inches.
Gap-chord ratio: .87.
UPPER PLANE.
(Including center section.)
Span: 32 feet 1 inch .
Chord: 71 .5 to 30 inches.
Area, with a ilerons: 165.2.
I ncidence, degrees : Root 0°; R . H . 30', L. H. 10'.
Landing gear: Area- 6.3 square feet.
Chord: 18 inches.
83931-24 (l)
LOWER PLANE.
Span : 22 feet 6 in ches.
Chord: 58 inches to 0.
Area: 81.5 .
Incidence : Root 0°, t ip + 20 feet .
Diheclra l: 1° 23' lower surface.
AlLli!RO NS O il F LAPS.
Number: 2.
Arrangement : Trailing edge, upper wing tips.
Upper lengt h : 8 feet 10 inches.
Upper chord: 8.5 inches to 12 inches.
Upper area: 14.76 square feet.
Lower length: None.
Distance from center a ilerons to longitudinal axis of
airplane: 117 inches.
CENTER SE CTIO N.
Area: None.
STARlLi l'ER.
Area: 20 square feet.
Setting : Acljustable 3° to -3°.
Chord : 30 inches.
E J,E VA'rOR.
Area : 11 .0 square feet.
2
Distance from leading edge of elevator to center of
gr:1Yity of airpl[tne : 181.6 in ches.
R U DDER.
Area: 5.73 square feet.
Distance from leading edge of rudder to center of
gra\•ity of a irplane: 18-±.6 inches.
LANDI NG GEAR.
Number of wheels : 2.
Tread: 5 feet 51 inches.
Shock-absorbing system: E lastic cord.
Braking device: Tail skid.
Wheels a head of center of graY ity: 19.4 inches.
FIN' .
..\rea : 3.88 square feet.
D ESCRIPTION OF POWER PLANT.
ENGINE .
Make: Curfo;~ D-1 '.l.
Fa c tor~· No.: 12.
A. S. No.: 10109.
Type: WC. " V " di rect driYe.
~umber in plane: One.
Location: Nose of fuselage.
Rated horsepo1rnr : 375.
Rated revolutions per minute : 2,000.
Bore: 4.5 inches .
Strok e: 6 inches.
Compression ratio: 5.3 : 1.
Weight, dry : 671. .
Gas consumption : 53 pounds horsepower per hour.
Oil consumption : .015 pounds horsepower per hour.
Weight of water in engine: 44 pounds.
Remarks : Displacement, 1,145 cubic inches . Economical
revolu t ions per minute, 1,850.
IGNITION.
Battery or magneto: 1agneto.
Make: Splitdorf.
Number :· Two.
Advance, degrees: L. 28°, R. 32°.
Gas interrupter: .020.
Distributor: J ump spark.
Plugs, make : A. C.
Type: Porcela in.
Gap: .015.
CARB U flE:TORS .
Make: Stromberg.
Type : NAY5.
Number: Two.
Setting jet: 45 Main 29 Air Bleed .
Choke: lH .
Compensator: None.
Gas drains: Direct from scoop to bottom of fuselage.
Air intake: Vert ical scoop .
Mixture control : I ntegral.
Effective to altitude: Yes.
Remarks : New carbu retor. No tes t~ from P. P . lab.
to date.
Make : Boeing.
Type : Tunnel.
Number: One.
RADI ATORS .
Cor e : A. S. standard 9 inc hes.
Position : Below engine.
Fronta l a rea : 2.45 square feet.
Depth: 9 inches.
Length : 16.5 inches.
Width: Core 23f inches.
Radiator surface: 218 square feet.
Temperature adjustment : Shutters.
Water capacity: 44.8 pou nds.
Flow, at 2.5 head : 57.5 ga llons per min ute.
Thermometers, make : Boyce.
·weight , empty : 92 pounds.
Type: " C."
Water ca.pa.city of whole system: 112 pounds, approximately.
EXHAUST P l PES .
Description: Div ided mani fold, 2 ea.ch side of
motor ; 1 staek to 3 c_\"linders. Stacks not ro iind b11t
streamli ned.
L UBRI CA'l'!ON.
Capacity, oil tank: 7 gallons.
Dimens ions, oil tank: Irregular.
Oil used (brand): Liberty.
Oil pressure: 100 pounds.
Oil temperature: 140° F. inlet .
Typepump: Gear.
Wet or d ry sump: Dry.
Descr iption, lubrication system: P ressure system.
FUEL SYSTEM.
Number of tanks: Two.
Location: Main-Fuselage. Gravity upper wing C/S.
Capacity, main pounds, 69 gallons, total 408 pounds.
Materia l: Crash proof.
Ga uge: Not known.
Description of fuel supply system: Ma.in tank ,
gravity tank, motor p nmp.
ENGINE CONTROL.
Description: Rod and lever.
PROPELLER.
Make: Curtiss climbing.
Number blades : Two.
Diameter: 8 feet 2 inches.
Pitch: 5 feet 10-H inches.
Manufacturer's No.: Number 1136.
A. S. No.: X- 29064.
Inspector: 02910.
Remarks : ·walnut.
PILOTS' OBSERVATIONS.
FLYING QUALITIES.
Taxying.-This plane taxies excellently even in
strong wind. This is due, no doubt, to a very effective
steerable tailskid.
'l'ake-ojj".- 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 p a ncake or
ground loop.
Stability.- This plane is stable laterally and directionally.
It is very slightly unstable longitudinally ,
which results in a slight hunting at high speeds. It is
3
not serious enough to interfere with proper sighting
of the guns, however.
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 ani:l 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.
LIEUT. BROOKLEY,
LIEUT. PEARSON,
LIEUT DOOLITTLE.
FIG. 1.
4
Fro.?
F IG. 3,
FIG . 4
5
80c!N6 Pt/RSt/IT 80c/NG Pl/li'.St//T
FIG. 5. FIG. 6.
0

Description

Title	Performance test of Boeing Pursuit, Type I equipped with Curtiss D-12 engine (performance test report no. 113)
Author	United States. Army. Air Service. Engineering Division.
Date Issued	1924-03-15
Series Information	Air Service information circular (Aviation) ; v. 5, no. 460; McCook Field report ; Serial no. 2227
Description	This document describes the Boeing Pursuit, Type I, airplane and gives the results of flight performance tests, including observations made by the test pilots related to taxiing, take-off, landing, stability, maneuverability, visibility, maintenance, and adaptability. Also included are drawings showing the biplane from four different angles.
Subject Terms	Biplanes; Boeing airplanes; Airplanes--Testing; Airplanes--Flight testing; Airplanes--Handling characteristics; Airplanes, Military
Report Publisher	Washington, D.C. : Chief of Air Service
File Name	asic460_ocr.pdf
Document Type	Text
File Format	PDF
File Size	4.27 Mb
Document Source	Auburn University Libraries. Government Documents.
Digital Publisher	Auburn University Libraries
Rights	This document is the property of the Auburn University Libraries and is intended for non-commercial use. Users of the document are asked to acknowledge the Auburn University Libraries.
Submitted By	Coates, Midge
OCR Transcript	Auburn University Libraries 1111111 1111111111111111111111111 1111111111111111111111111 1111111111111111111111 31706 025 85017 8 D REPOR T , SERI AL No . 2227 AIR SERVICE INFOR IRCULAR PUBLISHED BY THE CHIEF OF AIR SERVICE, WASHINGTON, D. C. Vol. V March 15, 1924 No. 460 PERFORMANCE TEST OF BOEING PURSUIT, TYPE I EQUIPPED WITH CURTISS D-12 ENGINE (PERFORMANCE TEST REPORT No. 11 3 ) Prepared by Engineering Division, Air Service McCook Field, Dayton, Ohio October 8, 1923 WASHINGTON r Ralph Brown Draughon t mfH\HY MAY ~i 4 Z013 Non-b.epgitory Aub,Utn University I GOVERNMENT PRINTING OFFICE 1924 CERTIFICATE: By direction of the Secretary of War the matter contained h erein is published as administrative information and is required for the proper transaction of the public business. (n) '/ PERFORMANCE TEST OF BOEING PURSUIT, TYPE I, EQUIPPED WITH CURTISS 0~ 12 ENGINE. OFFICIAL PERFORMANCE TEST- SUMMARY OF RESULTS. OcTOB}JR 8, 1923. Airplane: Boeing Pursuit. No. : (P-309) . Type: L Engine: Curtiss D- 12 (low compression) . Propeller: Curtiss Climbing X-29064. Equipped as : Pursuit. Weight empty (including water) _____ __ ___ ____ _ Armament and equipment _ ___ _______ __ _____ _ Armament: 215 pounds. Equipment: 55 pounds. Crew __ ______________ _____ - __ - _____ - - - - - - - - Gasoline: (Capacity 69 gallons, 408 pounds; bal-last 42 pounds) __________________________ _ Oil: (Capacity 6.5 gallons, 49 pounds; ballast 11 pounds ____ __________ ___ ___ ___ _____ __ _ Ponnds. 2, 011 270 180 450 60 Weight loaded __________ ___ ___ ______________ 2, 971 Weight per square foot, 11.74 pounds (253 square feet. Total area inclusive ailerons). Weight per horsepower, 6.76 pounds (440 horsepower at 2,380 revolutions per minute). (Horsepower estimated, test eng.) Stand- Climb. Speed. ard taul tdie- 'l'ime . Rate, Trne Flow, I f~~~- in min. R. p. m. f~h~.r speed. M. p. h. R.p.m. ~~~u~~r --- ---------- --------- - - 6 500 io:ooo 15,000 20,000 25, 000 1?2 000 222; 850 3. 8 6. 7 12. 8 24. 7 34. 9 2,130 2,090 21075 2, 055 2,040 1 Serv"ice ceilin g. 2,055 84. 5 160.9 2, 380 1, 365 86.6 1.54.3 2 330 1,025 88.6 150.2 2'.295 625 94. 7 142.9 2,235 270 105. 4 132. 2 2,135 100 111. 8 124. 0 2,070 0 115. 5 115. 5 2,030 2 Absolute ceiling. Endurance, full throttle at 10,000 (including climb): approximately 2 hours, 50 minutes. Minimum speed at sea-level (lowest throttle): 67 miles per hour at 1,355 revolutions per minute. Landing speed: 64 miles per hour. DISTRIBUTION OF WEIGHTS. Weight empty (with water) ____ ____ ______ __ ___ _ Armament and equipment _____ ____ ___ ______ _ Armament, 215. Equipment, 55. Crew _______ _________________ - -- - - - - - - - - - - - Gasoline: (Capacity 69 gallons, 408 pounds; bal-last 42 pounds) ___ _____ __ _______ _____ ____ _ Oil: (Capacity, 6.5 gallons, 49 pounds ; ballast, 11 pounds) ______ _____ __ ____ __ _____ _____ _ _ Ponnds. 2, Oll 270 180 450 60 Weight loaded ___ ____ __ ___ _______ _______ ____ 2, 971 Weight on front wheels (tail skid on ground) __ 2, 509 Weight on tail skid (tail skid on ground)____ ____ 462 Weight on front wheels (flying position) ________ 2, 681 Weight on tail skid (flying position)_ ____ ___ ____ 290 c~_nter of. ~ravity (distance from wheels in fly-mg pos1t10n) _ _ _ ___ _ _ ___ _ _ _ __ __ _ _ _ _ _ _ __ _ 19.4 Provisions for special equipment not carried during test. DESCRIPTION OF AIRPLANE. Dlil>IENSIONS. Over-all span: 32 feet 1 inch. Over-all length: 22 feet lOi inches. Over-all height: 8 feet 9 inches. In flying position: 5 feet 3 inches. AIRPLANES. Wing curve: Goettingen 436. Sweepback: Taper. Dihedral, degrees: Upper 1° lower surface. Stagger : 14° (11 inches). Total area, including ailerons: 253.05 square feet . Gap: Mean- 52 inches. Gap-chord ratio: .87. UPPER PLANE. (Including center section.) Span: 32 feet 1 inch . Chord: 71 .5 to 30 inches. Area, with a ilerons: 165.2. I ncidence, degrees : Root 0°; R . H . 30', L. H. 10'. Landing gear: Area- 6.3 square feet. Chord: 18 inches. 83931-24 (l) LOWER PLANE. Span : 22 feet 6 in ches. Chord: 58 inches to 0. Area: 81.5 . Incidence : Root 0°, t ip + 20 feet . Diheclra l: 1° 23' lower surface. AlLli!RO NS O il F LAPS. Number: 2. Arrangement : Trailing edge, upper wing tips. Upper lengt h : 8 feet 10 inches. Upper chord: 8.5 inches to 12 inches. Upper area: 14.76 square feet. Lower length: None. Distance from center a ilerons to longitudinal axis of airplane: 117 inches. CENTER SE CTIO N. Area: None. STARlLi l'ER. Area: 20 square feet. Setting : Acljustable 3° to -3°. Chord : 30 inches. E J,E VA'rOR. Area : 11 .0 square feet. 2 Distance from leading edge of elevator to center of gr:1Yity of airpl[tne : 181.6 in ches. R U DDER. Area: 5.73 square feet. Distance from leading edge of rudder to center of gra\•ity of a irplane: 18-±.6 inches. LANDI NG GEAR. Number of wheels : 2. Tread: 5 feet 51 inches. Shock-absorbing system: E lastic cord. Braking device: Tail skid. Wheels a head of center of graY ity: 19.4 inches. FIN' . ..\rea : 3.88 square feet. D ESCRIPTION OF POWER PLANT. ENGINE . Make: Curfo;~ D-1 '.l. Fa c tor~· No.: 12. A. S. No.: 10109. Type: WC. " V " di rect driYe. ~umber in plane: One. Location: Nose of fuselage. Rated horsepo1rnr : 375. Rated revolutions per minute : 2,000. Bore: 4.5 inches . Strok e: 6 inches. Compression ratio: 5.3 : 1. Weight, dry : 671. . Gas consumption : 53 pounds horsepower per hour. Oil consumption : .015 pounds horsepower per hour. Weight of water in engine: 44 pounds. Remarks : Displacement, 1,145 cubic inches . Economical revolu t ions per minute, 1,850. IGNITION. Battery or magneto: 1agneto. Make: Splitdorf. Number :· Two. Advance, degrees: L. 28°, R. 32°. Gas interrupter: .020. Distributor: J ump spark. Plugs, make : A. C. Type: Porcela in. Gap: .015. CARB U flE:TORS . Make: Stromberg. Type : NAY5. Number: Two. Setting jet: 45 Main 29 Air Bleed . Choke: lH . Compensator: None. Gas drains: Direct from scoop to bottom of fuselage. Air intake: Vert ical scoop . Mixture control : I ntegral. Effective to altitude: Yes. Remarks : New carbu retor. No tes t~ from P. P . lab. to date. Make : Boeing. Type : Tunnel. Number: One. RADI ATORS . Cor e : A. S. standard 9 inc hes. Position : Below engine. Fronta l a rea : 2.45 square feet. Depth: 9 inches. Length : 16.5 inches. Width: Core 23f inches. Radiator surface: 218 square feet. Temperature adjustment : Shutters. Water capacity: 44.8 pou nds. Flow, at 2.5 head : 57.5 ga llons per min ute. Thermometers, make : Boyce. ·weight , empty : 92 pounds. Type: " C." Water ca.pa.city of whole system: 112 pounds, approximately. EXHAUST P l PES . Description: Div ided mani fold, 2 ea.ch side of motor ; 1 staek to 3 c_\"linders. Stacks not ro iind b11t streamli ned. L UBRI CA'l'!ON. Capacity, oil tank: 7 gallons. Dimens ions, oil tank: Irregular. Oil used (brand): Liberty. Oil pressure: 100 pounds. Oil temperature: 140° F. inlet . Typepump: Gear. Wet or d ry sump: Dry. Descr iption, lubrication system: P ressure system. FUEL SYSTEM. Number of tanks: Two. Location: Main-Fuselage. Gravity upper wing C/S. Capacity, main pounds, 69 gallons, total 408 pounds. Materia l: Crash proof. Ga uge: Not known. Description of fuel supply system: Ma.in tank , gravity tank, motor p nmp. ENGINE CONTROL. Description: Rod and lever. PROPELLER. Make: Curtiss climbing. Number blades : Two. Diameter: 8 feet 2 inches. Pitch: 5 feet 10-H inches. Manufacturer's No.: Number 1136. A. S. No.: X- 29064. Inspector: 02910. Remarks : ·walnut. PILOTS' OBSERVATIONS. FLYING QUALITIES. Taxying.-This plane taxies excellently even in strong wind. This is due, no doubt, to a very effective steerable tailskid. 'l'ake-ojj".- 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 p a ncake or ground loop. Stability.- This plane is stable laterally and directionally. It is very slightly unstable longitudinally , which results in a slight hunting at high speeds. It is 3 not serious enough to interfere with proper sighting of the guns, however. 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 ani:l 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. LIEUT. BROOKLEY, LIEUT. PEARSON, LIEUT DOOLITTLE. FIG. 1. 4 Fro.? F IG. 3, FIG . 4 5 80c!N6 Pt/RSt/IT 80c/NG Pl/li'.St//T FIG. 5. FIG. 6. 0

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