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.MChart
B.H.P.
Throttle
Position
Test
Condition
Mixture

 13,000   382.030001110Wide openWing guns coveredMax. power
 13,00037030001110Wide openWing guns uncoveredMax. power
 13,00037930001005Wide openWing guns coveredAuto Rich   
 12,7003652600  993Wide openWing guns coveredMax. power
 12,7003632600  978Wide openWing guns coveredMax. power

  3.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
RPMChart
B.H.P.
Rate of Climb
Ft./Min.
Time of Climb
Min.

          0178   300010502200      0
   5,000194   3000109522702.24
 10,000208   3000114023454.41
 11,375212   3000110022905.00
 15,000222   2600  82015707.06
 20,000236   2600  680107010.91  
 25,000248.52600  555  61017.03  
 S/C 30,800       262.52600-  10038.96  
 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 Altitude366 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.MB.H.P.Throttle
Position
Test
Condition
Mixture

   5,10036330001150Part2-CannonsAuto Rich
 *12,650  39630001150Wide Open2-CannonsAuto Rich
 12,65039030001130Wide Open4-CannonsAuto Rich
 12,75037426001000Wide Open2-CannonsAuto 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.

  3.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
RPMStd.
B.H.P.
Rate of Climb
Ft./Min.
Time of Climb
Min.

          0158300011502460      0
   5,0001703000115028901.87
 10,0001833000109529403.51
 13,9001933000  94523005.00
 15,000  195.52600  81018405.58
 20,0002072600  68512908.82
 25,0002182600  570  77013.77  
 30,0002302600  470  27024.29  
 S/C 31,350       -2600-  10033.84  
 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
RPMb.h.p.Gross
Weight
Throttle

   5000394300014807865Part
   5000  357.5300011257452Part
 *10,400  415300014807795Full
 10,400377300011257312Part
 **17,500    408300011257730Full
 25,10039530008367617Full

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

  7.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
RPMb.h.p.Rate of
Climb
Ft/Min.
Time of
Climb
Min.

 Sea Level157300012403000      0
   5,000169300012803140  1.63
   * 9,800  181300013203260  3.13
 15,000192300010902610  4.87
 20,0002023000  9101980  7.06
 25,000   213.53000  760135010.09
 30,000   225.53000  620  72015.08
 S/C 35,100       --3000--  10031.01
 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 place376.5 MPH
    b.Camera blister removed; fishtail stacks in place379.0 MPH
    c.Blister removed; standard stacks in place380.5 MPH
    d.Same as c., plus cleaned up condition385.0 MPH
    e.Same as d., with airplane sanded388.5 MPH

  2.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
RPMBHPThrottle
Position

   4,300369.53,0001,175Part
 *12,500  388.53,0001,200Wide Open
 17,500386.03,000  975Wide Open
 24,800367.03,000  710Wide Open

*Critical altitude for military rated power.

  5.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
RPMStd. BHPRate of climb
Ft/Min
Time of climb
Min.

 01583,0001,150-0  
   5,0001703,0001,1502,6502  
   7,0001763,0001,1502,780   2.75
 10,0001843,0001,0402,460
 12,5001873,000   9552,200
 15,0001942,600   7701,600  6.5
 20,0002052,600   6401,13010.0
 25,0002172,600   520   67015.5
 S/C 31,300       2312,600-   10036.0
 A/C 32,600       2342,600-       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.

AltitudeUnpolished Camouflage
Paint Finish
Sanded and Polished
Camouflage Paint Finish
Man. Pr.
"Hg.
B.H.P.True Speed
M.P.H.
Man. Pr.
"Hg.
B.H.P.True Speed
M.P.H.
13,00046.6120039547.21220401   
18,00038.4  98238839   1000394.5

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.

EngineBoost
limitations
Max. T.A.S.
at 1000 ft.
Max T.A.S. at respective
full throttle heights.
F.3.R56" 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.R51" 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.

EngineMax. rate of climbTime to 20,000'Service ceiling
F.3.R1890 ft/min at 11,500 ft.12.05 mins.30,000 ft.
F.21.R1930 ft/min at 7,20014.90 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 level37858.837458.0
1,000 ft.37856.637455.9
10,000 ft.37041.436640.8

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

EngineMax. TAS
   (mph)   
Height
   (ft)   
F.4R401 4,400
F.20R40910,000

Climb

EngineMax. rate of climbTime to 20,000Service ceiling
F.4R4,090 ft/min. at 800 ft.8.1 mins.31,500 ft.
F.20R3,800 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

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