Mustang (Allison Engine) Performance Trials

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

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, MATERIAL DIVISION
Wright Field, Dayton, Ohio
June 16, 1942
P-51, AAF No. 41-37320
Performance Tests

Summary
        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
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

ARMY AIR FORCES
MATERIAL CENTER
Wright Field, Dayton, Ohio
April 2, 1943
P-51A-1-NA, AAF No. 43-6007
Flight Tests

Summary
        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 --

For the full report see HERE
P-51A-1 Airplane - Official Performance Curves

ARMY AIR FORCES
MATERIAL COMMAND
Wright Field, Dayton, Ohio
20 July 1943
P-51, AAF No. 41-37320
Comparitive Performance Tests

Summary
        High speed tests

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

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

  Report of Spin Tests, P-51 & P-51A   British Army Cooperation Tactical Employment of the Mustang I (P-51).
Merlin Engined Mustang Performance Trials   Main
� 2005  WWIIaircraftperformance.org  All Rights Reserved

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.

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.

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

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	-	-	-

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

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	--

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

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	-

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.)

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.

	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

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.