P-51 Mustang (Allison Engine) Performance Trials

P-51 Mustang (Allison Engine) Performance Trials

North American Aviation, Inc.
Inglewood, California
April 24, 1940

Model Specification for
Model XP-51 Airplane
(N.A.A. Model No. NA-73)
Report No. 1620

Summary

Performance (with Design Useful Load)

High Speed at S. L. (Present Military Rating)	316 MPH
High Speed (Present Military Rating)	375.5 M.P.H. at 16,500 Ft.
High Speed (Future Military Rating)	384 M.P.H. at 19,000 Ft.
Maximum Rate of Climb (Military Rating)	2720 Ft./Min.
Time to Climb to 20,000 Ft. (Military Rating)	8.80 Mins.
Service Ceiling	32,000 Ft.

For more of this report see HERE

WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
December 27, 1941

MEMORANDUM REPORT ON
Pursuit Single Engine XP-51 A.C. No. 41-38

Subject: Performance

Section: Flying Branch

Serial No: PHQ-M-19-1330-A

Summary

A.	Purpose

	1.	Report on performance of North American XP-51. Airplane equipped with Allison V-1710-39 engine (backfire screens in intake ports) and 3-bladed constant speed propeller, blade design No. 614CC1.5-18. Gross weight as tested approximately 7934 lbs. Landing gear retracted; wing flaps neutral; radio antenna installed; prestone and oil shutters flush with cowling in level flight, 1/4 open in climb; four .30 cal. and two .50 cal. guns in wings and two .50 cal. guns in fuselage. Test with wing gun openings covered and uncovered.

B.	Test Results

	1.	High Speed tests.


Altitude ft.	True Speed MPH	R.P.M	Chart B.H.P.	Throttle Position	Test Condition	Mixture

13,000	382.0	3000	1110	Wide open	Wing guns covered	Max. power
13,000	370	3000	1110	Wide open	Wing guns uncovered	Max. power
13,000	379	3000	1005	Wide open	Wing guns covered	Auto Rich
12,700	365	2600	993	Wide open	Wing guns covered	Max. power
12,700	363	2600	978	Wide open	Wing guns covered	Max. power

Climb data, propeller set for 3000 R.P.M. for first five mins. with throttle open to 44" Hg. manifold pressure or wide open when below. Wing gun openings covered.


Altitude Ft.	True Speed MPH	RPM	Chart B.H.P.	Rate of Climb Ft./Min.	Time of Climb Min.

0	178	3000	1050	2200	0
5,000	194	3000	1095	2270	2.24
10,000	208	3000	1140	2345	4.41
11,375	212	3000	1100	2290	5.00
15,000	222	2600	820	1570	7.06
20,000	236	2600	680	1070	10.91
25,000	248.5	2600	555	610	17.03
S/C 30,800	262.5	2600	-	100	38.96
A/C 31,900	-	2600	-	-	-

For the full report see HERE

North American Aviation, Inc.
Inglewood, California
May 1, 1942

Model Specification for
Model A-36 Airplane
(N.A.A. Model No. NA-97)
Report No. NA-5338

Summary

Performance (Military Rating)

High Speed at S. L.	345 MPH
High Speed at Critical Altitude	366 MPH at 5775 Ft.
Maximum Rate of Climb	3290 Ft./Min.
Time to Climb to 10,000 Ft.	3.54 Mins.
Service Ceiling	30,000 Ft.

For more of this report see HERE

WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
June 16, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-51 A.C. No. 41-37320

Subject: Performance Tests

Section: Flight Section

Serial No: PHQ-M-19-1415-A

Summary

A.	Purpose

	1.	To report on performance of first production model of North American P-51 airplane, A.C. No. 41-37320. Airplane equipped with Allison V-1710-39 engine with individual intake port screens removed and T-type manifold screens installed; carburetor flange screen and air filter removed; carburetor intake screen made of parallel vertical wires .05 inches in diammeter and laced thru scoop approximately 5/16 inches part. Equipped with a three-bladed constant speed propeller, blade design No. 89301-6, blade angle range 23° to 58° at 42 inch radius. Gross weight as tested approximately 8114 pounds; c.g. location wheels down 27.49 percent m.a.c. with two cannons in place, and a gross weight of 8824 pounds with four cannons and armour plate in place. Landing gear retracted, wing flaps neutral; radio antenna installed; prestone and oil shutters flush with cowling in level flightl 1/4 open in climb; carburetor cold.

		Power Curve used V-1710-39 dated December 12, 1941

B.	Test Results

	1.	High Speed tests.


Altitude feet	True Speed mph	R.P.M	B.H.P.	Throttle Position	Test Condition	Mixture

5,100	363	3000	1150	Part	2-Cannons	Auto Rich
*12,650	396	3000	1150	Wide Open	2-Cannons	Auto Rich
12,650	390	3000	1130	Wide Open	4-Cannons	Auto Rich
12,750	374	2600	1000	Wide Open	2-Cannons	Auto Rich

*Critical altitude for military rated power. It will also be noted that the critical altitude for normal rated power is at practically the same level. Possible explanations for that relationship is that the carburetor ram pressure decreases slightly at engine speeds above 2600 RPM or that the engine power curves or in error.

Climb data: propeller set for 3000 R.P.M. for first five minutes with throttle open to give 1150 BHP or wide open when below. Climb with two-cannon installation.


Altitude Feet	True Speed MPH	RPM	Std. B.H.P.	Rate of Climb Ft./Min.	Time of Climb Min.

0	158	3000	1150	2460	0
5,000	170	3000	1150	2890	1.87
10,000	183	3000	1095	2940	3.51
13,900	193	3000	945	2300	5.00
15,000	195.5	2600	810	1840	5.58
20,000	207	2600	685	1290	8.82
25,000	218	2600	570	770	13.77
30,000	230	2600	470	270	24.29
S/C 31,350	-	2600	-	100	33.84
A/C 32,800	-	2600	-	-	-

For the full report see HERE

Data from this report was used in: Compartive Performance of P-39D, P-40F, and P-51 Airplanes

PROOF DEPARTMENT
TACTICAL COMBAT SECTION
ARMY AIR FORCES PROVING GROUND COMMAND
EGLIN FIELD, FLORIDA
30 December 1942

FINAL REPORT
ON
TACTICAL SUITABILITY OF THE P-51 TYPE AIRPLANE

Conclusions

It is concluded that:

a. The subject aircraft is the best low altitude American fighter aircraft yet developed, and should be used as the criterion for comparison of subsequent types.

b. If possible, the power loadings of this fighter aircraft should be materially reduced, without increasing the wing loading.

c. To reduce the power loadings of the aircraft, excess weight in the structure, and accessories not vital to operational use should be eliminated, and engine performance increased.

d. Pilots become completely at home in this aircraft immediately after the first take-off due to the remarkable sensitivity of control, simplicity of cockpit, and excellent flying characteristics.

e. The rate of roll is not as rapid as is desired for combat operations.

f. The view downward over the nose is not sufficient to allow full deflection shooting in a turn.

g. The automatic manifold pressure regulator is completely satisfactory.

h. With the exception of the radiators, the airplane is completely satisfactory.

i. The range of speeds obtainable in the throttle limits in level flight is excellent.

j. Up to fifteen-thousand (15,000) feet this is faster than all standard American fighters with the exception of the P-47C-1.

For the full report see HERE

WAR DEPARTMENT
ARMY AIR FORCES, MATERIEL DIVISION
Wright Field, Dayton, Ohio
April 2, 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-51A-1-NA, AAF No. 43-6007

Subject: Flight Tests

Section: Flight Test

Serial No: PHQ-M-19-1576-A

Summary

A.	Purpose

	1.	Report on flight tests of North American P-51A-1-NA, airplane at the manufacturer's plant. Airplane equipped with Allison V-1710-81 engine and a three-bladed Curtiss Electric constant speed propeller, blade design No. 89303-27W, blade angle range 28° to 58° at 42 inch radius. Gross weight at take-off was 8000 lbs. with c.g. at 27.75 percent m.a.c., wheels down. Loading was based on total useful load of 1549 lbs. including pilot and parachute, 105 gallons fuel, 7.5 gallons oil, four .50 caliber wing guns and accessories, 270 rounds of ammunition per gun, gun sight, gun camera, pistol, incendary grenade, and intrapped fuel and oil (52 lbs.). Landing gear retracted; wing flaps neutral; carburetor cold; mixture auto-rich unless otherwise specified; radio mast and antenna wire (strung from mast to top of fin) installed; blast tube openings covered; shell ejection port open on right wing, covered by temperature bulb on left wing; shell clip ejection ports open; camouflage finish sanded with No. 400 sandpaper until smooth. Horsepowers obtained from power curve V-1710-81, -83, and -85, dated October 28, 29, 1942 (2:1 propeller gear ratio; 9.6:1 blower gear ratio).

B.	Test Results

	1.	High speeds, prestone and oil cooler shutter in faired position.


Altitude Feet	Speed MPH	RPM	b.h.p.	Gross Weight	Throttle

5000	394	3000	1480	7865	Part
5000	357.5	3000	1125	7452	Part
*10,400	415	3000	1480	7795	Full
10,400	377	3000	1125	7312	Part
**17,500	408	3000	1125	7730	Full
25,100	395	3000	836	7617	Full

	*Critical altitude for war emergency power in level flight.
	**Critical altitude for military rated power in level flight.

Climb data: Prestone and oil cooler shutters wide open, mixture control in the auto-rich position, throttle set for 52 inches Hg. at 3000 RPM or wide open when below.


Altitude Feet	Airspeed MPH	RPM	b.h.p.	Rate of Climb Ft/Min.	Time of Climb Min.

Sea Level	157	3000	1240	3000	0
5,000	169	3000	1280	3140	1.63
* 9,800	181	3000	1320	3260	3.13
15,000	192	3000	1090	2610	4.87
20,000	202	3000	910	1980	7.06
25,000	213.5	3000	760	1350	10.09
30,000	225.5	3000	620	720	15.08
S/C 35,100	--	3000	--	100	31.01
A/C 36,000	--	3000	--	0	--

*Critical altitude for military power in climb.

(Click to enlarge)

For the full report see HERE

ARMY AIR FORCES
MATERIEL COMMAND
Wright Field, Dayton, Ohio
July 20, 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-51, AAF No. 41-37320

Subject: Comparitive Flight Tests

Section: Flight

Serial No: ENG-19-1622-A

Summary

A.	Purpose

	1.	To report results of performance tets on P-51, AAF No. 41-37320, run at Wright Field. Airplane equipped with V-1710-39 engine with T manifold screens; three bladed, constant speed propeller, blade design No. 89301-6. Four cannons and armor plate in place. Gross weight at take-off as tested was 8,849 pounds with camera in, and 8,824 pounds with camera removed. Landing gear retracted, wind flaps neutral, radio antenna installed, prestone and oil cooler scoop closed.

B.	Test Results

	1.	With several configurations the following high speeds were obtained at 3,000 RPM, wide open throttle, and 1,200 b.h.p. at 12,500 feet:

a.	Camera blister in place; fishtail stacks in place	376.5 MPH
b.	Camera blister removed; fishtail stacks in place	379.0 MPH
c.	Blister removed; standard stacks in place	380.5 MPH
d.	Same as c., plus cleaned up condition	385.0 MPH
e.	Same as d., with airplane sanded	388.5 MPH

High speed tests; same configuration as paragraph e, mixture auto-rich.

Poor fitting cowling smoothed up, antenna wires to horizontal stablizer removed, rear windows secured flush, gun access doors secured, rough sections repainted and cracks filled. Camouflage paint fairly smooth at this time due to normal wear.


Altitude Feet	True Speed	RPM	BHP	Throttle Position

4,300	369.5	3,000	1,175	Part
*12,500	388.5	3,000	1,200	Wide Open
17,500	386.0	3,000	975	Wide Open
24,800	367.0	3,000	710	Wide Open

*Critical altitude for military rated power.

Climb data: Propeller set for 3,000 RPM for first five minutes with throttle open to give 1,150 BHP or wide open when below; mixture auto-rich:


Altitude Feet	True Speed MPH	RPM	Std. BHP	Rate of climb Ft/Min	Time of climb Min.

0	158	3,000	1,150	-	0
5,000	170	3,000	1,150	2,650	2
7,000	176	3,000	1,150	2,780	2.75
10,000	184	3,000	1,040	2,460	4
12,500	187	3,000	955	2,200	5
15,000	194	2,600	770	1,600	6.5
20,000	205	2,600	640	1,130	10.0
25,000	217	2,600	520	670	15.5
S/C 31,300	231	2,600	-	100	36.0
A/C 32,600	234	2,600	-	0	-

For the full report see HERE

ARMY AIR FORCES
MATERIEL COMMAND
Wright Field, Dayton, Ohio
16 September 1943

P-51, AAF No. 41-37320
Speed Tests

Summary

High speed at wide open throttle.

Altitude	Unpolished Camouflage Paint Finish			Sanded and Polished Camouflage Paint Finish
Altitude	Man. Pr. "Hg.	B.H.P.	True Speed M.P.H.	Man. Pr. "Hg.	B.H.P.	True Speed M.P.H.
13,000	46.6	1200	395	47.2	1220	401
18,000	38.4	982	388	39	1000	394.5

For the full report see HERE

Aeroplane and Armament Experimental Establishment
Boscombe Down
19 May 1942

Mustang AG.351
(Allison V-1710 F.3.R.)
Brief Performance Trials

Summary

Climb: The best rate of climb was 1,980 feet/minute at 11,300 feet. The estimated absolute ceiling is 31,000 feet and the Service ceiling is 30,000 feet with the radiator intake scoop and exit duct in the minimum drag position. The best climbing speed is 170 m.p.h. A.S.I. up to 11,000 feet and then reducing speed by 2 m.p.h. A.S.I. per thousand feet.

Level speeds: The maximum all-out level speed was 370 m.p.h. true air speed at 15,000 feet with the radiator blanks removed. With the various blanks fitted this speed was lowered by 13 m.p.h. and the full throttle height fell to 14,700 feet due to the decreased effect of ram brought about by the decrease in speed.

For more of this report see HERE

[Weights and Loading data] [Handling trials]

Aeroplane and Armament Experimental Establishment
Boscombe Down
31 March 1943

Mustang A.P.222
(Allison V-1710 F.3.R & F.21.R)
Climb and level speed performance

Summary

Level speeds.

Engine	Boost limitations	Max. T.A.S. at 1000 ft.	Max T.A.S. at respective full throttle heights.
F.3.R	56" Hg.	360 m.p.h.	392 m.p.h. at 7,900 ft.
"	44.5" Hg.	328 m.p.h.	384 m.p.h. at 13,700 ft.
"	42" Hg.	317 m.p.h.	381 m.p.h. at 15,250 ft.
F.21.R	51" Hg.	366 m.p.h.	377 m.p.h. at 4,000 ft.
"	Full throttle (No limit)	377 m.p.h. (Boost 56.8" Hg.)	377 m.p.h. at Sea level (Boost 59" Hg.)

Climb.

Engine	Max. rate of climb	Time to 20,000'	Service ceiling
F.3.R	1890 ft/min at 11,500 ft.	12.05 mins.	30,000 ft.
F.21.R	1930 ft/min at 7,200	14.90 mins.	25,000 ft.

For more of this report see HERE

Aeroplane and Armament Experimental Establishment
Boscombe Down
2 June 1943

Mustang A.P.222
(Allison V-1710 F21R)
Level speed measurments
with a standard and modified induction manifold

Summary

	Modified manifold fitted		Standard manifold fitted
Standard height (feet)	Max. T.A.S. m.p.h.	Max. Boost Ins. Hg.	Max. T.A.S. m.p.h.	Max. Boost Ins. Hg.
Sea level	378	58.8	374	58.0
1,000 ft.	378	56.6	374	55.9
10,000 ft.	370	41.4	366	40.8

For more of this report see HERE

Aeroplane and Armament Experimental Establishment
Boscombe Down
3 April 1944

Mustang II FR.893
(Allison V-1710 F4R & F20R)
Climb and level speed performance

Summary

Level speeds

Engine	Max. TAS (mph)	Height (ft)
F.4R	401	4,400
F.20R	409	10,000

Climb

Engine	Max. rate of climb	Time to 20,000	Service ceiling
F.4R	4,090 ft/min. at 800 ft.	8.1 mins.	31,500 ft.
F.20R	3,800 ft/min. at 6000 ft.	6.9 mins.	34,000 ft.

For more of this report see HERE

Supplemental

Memorandum Report Eng-19-1615-A on P51 No. 41-37427 & P-51A No. 42-6009: Report of Spin Tests

Memorandum Report Eng-19-1621-A on P-51A No. 42-6009: Report of Power-on Spin Tests

XP 51 Dive Tests

Power Required and Power Available for the P-51A, P-51B and P-47B Airplanes.

A-36 Specific Operating Instructions

High speed of XP-51 airplane with V-1710-61 engine Chief, Aircraft Labortory, January 15, 1942.

Production of P-51 Mustang Fighter Airplanes. North American Aviation, Inc., February 2, 1942.

P-51 and Mustang Airplanes Aileron Effectiveness Chief, Production Engineering Section, October 3, 1942.

British Army Cooperation Tactical Employment of the Mustang I (P-51).

Pilot's Notes, Mustang I Aeroplane, Allison V-1710 F.3R Aero-Engine

Merlin Engined Mustang Performance Trials Main