P-40 Performance Tests

WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
March 14, 1941

MEMORANDUM REPORT ON
Pursuit Interceptor XP-40, A.C. No. 38-10

Subject:      Comparative speed tests
Section:      Flying Branch
Serial No:   PHQ-M-19-1206-A

SUMMARY

A.Purpose
 
  1.To report on comparative speed tests on the XP-40 airplane, A.C. No. 38-10, with three sets of exhaust stacks. Airplane equipped with Allison V-1710-19 engine and with three-bladed constant speed propeller, blade design No. 614cc1.5-12, blade angle range 25 to 49.5 degrees at 42 inch radius. All tests with wheels up, flaps neutral, cabin closed, carburetor cold, cowl flaps closed and with mixture auto-rich. Three sets of exhaust were used:- (1) Standard XP-40 exhaust stacks (one 2-1/4 inch diamter opening per cylinder); (2) Materiel Division exhaust stacks, Dwg. No. X-40D3857; (3) Materiel Division exhaust stacks, Dwg. No. X-40G1720 (not interconnected).
 
B.Factual Data
 
  1.Speeds for all three sets of exhaust stacks at 11,600 ft.:

 
 B.H.P.R.P.M.Throttle
Position
Speeds - M.P.H.
 
 Standard
Stacks
X-40D3857
Stacks
X-40G1720
Stacks
 
 10202600W.O.335332330
   9002600Part320318315
   8002600Part306305302

For the full report see HERE


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
July 28, 1941

MEMORANDUM REPORT ON
Pursuit Interceptor XP-40, A.C. No. 38-10

Subject:      Speed Test with Standard Exhaust Stacks
Section:      Flying Branch
Serial No:   PHQ-M-19-1273-A

SUMMARY

A.Purpose
 
  1.To report on speeds on the XP-40 with standard exhaust stacks. Airplane equipped with V-1710-33 engine and three-bladed, constant speed propeller, blade design No. 614cc1.5-12. All tests with wheels up, flaps neutral, cabin closed, carburetor cold, cowl flaps closed and mixture auto-rich.
 
B.Factual Data
 
  1.Critical altitude for rated horse power is 13,800 ft. for 960 bhp at 2600 rpm.
 
  2.Speeds at 11,600 ft. for comparison with test exhaust stacks (Ref. Mem. Report No. PHQ-M-19-1206-A):

 
 B.H.P.R.P.M.True Airspeed
MPH
 
 10202600335
   9002600320
   8002600307

For the full report see HERE

See also:Memorandum Report PHQ-M-19-1296-A on XP-40 No. 38-10: Speed Tests
 Memorandum Report PHQ-M-19-1299-A on XP-40 No. 38-10: Speed Tests


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
August 12,1940

MEMORANDUM REPORT ON
Pursuit 1-Engine P-40, A.C. No. 39-165

Subject:      Speed Tests
Section:      Flying Branch
Serial No:   PHQ-M-19-1125-A

SUMMARY

1.Purpose
 
  a.To report on speed tests pm Pursuit 1-engine (P-40) airplane, A.C. No. 39-165, with and without leading edge blisters in place. Airplane equipped with Allison V-1710-33 engine and 3-bladed constant speed propeller, blade design No. 614CC1.5-12, blade angle range 24° to 49° at 42 inch radius. Airplane camouflaged and flown with normal military load, landing gear retracted, wing flaps neutral, cabin and ventilators closed, carburetor cold, radiator shutters in neutral position. Cabin ventilator intake hole in leading edge of right wing open in test without blisters in place but covered in test with blisters.
 
2.Factual Data
 
  a.Tests at 15,000 ft. and 2770 r.p.m.:

 
 B.H.P.True Speed
No Blisters MPH
True Speed
Blister in Place MPH
Speed Lost Due
to Blisters MPH
 
 950335   329   6.0
 900329   323.55.5
 800314.5310   4.5
 700298.0294   4.0

For the full report see HERE


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
April 26, 1941

MEMORANDUM REPORT ON
Pursuit Interceptor P-40B, A.C. No. 41-5205

Subject:      Flight Test at Manufacturer's Plant
Section:      Flying Branch
Serial No:   PHQ-M-19-1227-A

SUMMARY

A.Purpose
 
  1.Flight test at the manufacturer's plant of the Curtiss P-40B airplane equipped with Allison V-1710-33 engine and 3-bladed, constant speed propeller, blade design No. 89301-3. Gross weight 6835 lbs. Landing gear retracted, cabin and ventilators closed, carburetor cold, wing guns in place, blast tubes for synchronized guns in place, radio antenna in place. Airplane camouflaged.
 
B.Factual Data
 
  1.High speed at 15,000 ft. at wide open throttle was 352 mph at 1090 bhp at 3000 rpm, radiator shutters neutral.
 
  2.High speed at 5000 ft. was 319 mph at 1085 bhp at 3000 rpm, radiator shutters neutral.
 
 3.High speed at 2600 rpm at 15,000 ft. at wide open throttle, was 331.5 mph at 920 bhp, radiator shutters neutral.
 
 4.Speed at rated power at 5000 ft. was 307 mph at 950 bhp at 2600 rpm, radiator shutters closed one notch from neutral position.
 
 5.Crusing data at 15,000 ft., radiator shutters closed two notches from neutral position.

 
 True Speed MPHR.P.M.B.H.P.% Rated BHP
 
 310228072075   
 286220060062.5
 258210048050   
 236200040041.7

   Climb data, radiator shutters wide open:

 
 Altitude
Ft.
Rate of Climb
Ft/Min
R.P.M.B.H.P.True Airspeed
MPH
Time
Min.
 
           0290030009521430   
   5,000298530001002  1551.7
 10,000307030001050  167  3.35
 14,750261030009551765   
 15,00021602600835176  5.11
 20,000152026007001837.9
 25,000  935260058518912.0  
 30,000  360260049019520.3  
 32,400  1002600--32.0  
 33,300      02600---

For the full report see HERE


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
July 21, 1941

MEMORANDUM REPORT ON
Pursuit Single Engine P-40D, A.C. No. 40-362

Subject:      Acceptance Performance Tests
Section:      Flying Branch
Serial No:   PHQ-M-19-1267-A

SUMMARY

A.Purpose
 
  1.Report on flight tests conducted at the manufacturer's plant on Curtiss P-40D. Airplane equipped with Allison V-1710-39 engine and 3-bladed constant speed propeller, blade design No. 89301-3, blade angle range 24.5° to 54.5° at 42" radius. Gross weight as tested 7740 lbs., c.g. location, wheels up, 27.9% m.a.c.; whee;s up; wing flaps neutral; radio antenna installed; prestone and oil cooler flaps flush with cowling in level flight, wide open in climb; four 50 cal. wing guns and uncovered blast tubes in plane, except where otherwise stated.
 
B.Test Results
 
  1.Level flight speed tests:

 
 Altitude
Ft.
True Speed
MPH
R.P.M.B.H.P.Throttle
Position
 
  *5,17532630001150Part
 *15,175  35430001085Wide
 15,1753352600910Wide
 15,175   307.52280725Wide
 15,1752902200  635Part
 15,1752652100  530Part
 15,1752391900  420Part
 15,1752091700  300Part

  4.Climb data, mixture control in automatic rich position:

 
 Altitude
Ft.
True Speed
MPH
R.P.M.B.H.P.Rate of Climb
Ft./Min.
Time of Climb
Min.
 
          01403000115025800   
          5151300011502580  1.94
 10,000162300011502580  3.88
 12,8501623000108023555.0
 15,000   172.52600  8401600  6.36
 20,0001822600  690112010.0  
 25,000   190.52600  560  63515.9  
 S/C 30,600           199.52600-  10035.0  
 A/C 31,600        2012600-      0-

For the full report see HERE


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
September 25, 1941

MEMORANDUM REPORT ON
Pursuit Single Engine P-40E, A.C. No. 40-384

Subject:      Performance
Section:      Flying Branch
Serial No:   PHQ-M-19-1300-A

SUMMARY

A.Purpose
 
  1.Report on performance of Curtiss P-40E. Airplane equipped with Allison V-1710-39 engine (backfire screens in intake ports) and 3-bladed constant speed propellers, blade design No. 89301-3. Gross weight as tested approximately 8011 lbs. with belly tank removed; c.g. location wheels up 28.5% m.a.c.; landing gear retracted; wing flaps neutral; radio antenna installed; prestone and oil cooler shutters flush with cowling in level flight, wide open in climb; six 50 cal. wing guns with uncovered openings in wings in place. Weight of belly tank and fuel 366 lbs. (capacity 52 gals.).
 
B.Test Results
 
  1.High speed tests:

 
 Altitude
Ft.
True Speed
MPH
R.P.M.B.H.P.Throttle
Position
Test Condition
 
 11,40034230001150WideBelly tank removed
 15,3003403000  990WideBelly tank removed
 15,3003193000  965WideBelly tank installed  
 15,3003162600  820WideBelly tank removed
 15,3002982600  800WideBelly tank installed  

  2.Climb data; propeller set for 3000 rpm for first 5 min. with throttle open tp 43.9" Hg. manifold pressure or wide when below.

 
 Altitude
Ft.
True Speed
MPH
R.P.M.B.H.P.Rate of Climb
Ft./Min.
Time of Climb
Min.
 
          0146   3000102021000
   5,000158.53000107022602.3
 10,000170.5300011202400  4.44
 11,300173.53000106522505.0
 15,000177.52600  7951370  7.38
 20,000187   2600  655  88011.82
 25,000196.52600  555  48019.42
 S/C 30,000        205   2600  470  10040.1  
 A/C 31,350        -2600-      0-

For the full report see HERE


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
April 5, 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-40E, A.C. No. 40-633

Subject:      Propeller Tests
Branch:       Flight test
Serial No:   FS-M-19-1580-A

SUMMARY

A.Purpose
 
  1.Report on performance of P-40E airplane, A.C. No. 40-633, equipped with four different propellers, each test being run with a propeller of particular blade design number, hub number, and spinner type as indicated. Airplane equipped with V-1710-39 engine and flown with wing flaps neutral, wheels up, carburetor cold, mixture "auto-rich" except where specified, cowl flaps neutral for level flaps and wide open for climbs. Airplane flown at a gross weight of approximately 8035 pounds with full gas and oil load, belly tank shackles in place, six .50 caliber guns without ammunition (no ballast), provision for spin chute but no spin chute in place. Horsepower figures obtained from power curve V-1710-39 dated December 12, 1941.
 
B.Test Results
 
  1.High Speeds in level flight.


PropellerAltitudeTrue Airspeed
MPH
b.h.pRPM

Hub C-532D
Blades 89301-3
Std. Spinner
14,900336.510002940
 
Hub C-5315S
Blades 618A
(Impregnated Wood)
Std. Spinner
15,13033210002940
 
Hub C-532D
Blades 89301-3 wth
De-icer Boots
Std. Spinner
15,13033310002940
 
Hub C-5315S
Blades 614ocl.5-12
Std. Spinner
15,130335.510002940

  3.Maximum rate of climb at wide open throttle and 2600 RPM.


   15,000 feet    19,000 feet    24,000 feet    28,000 feet  
PropellerR/C
F.P.M.
bhpVt
MPH
R/C
F.P.M.
bhpVt
MPH
R/C
F.P.M.
bhpVt
MPH
R/C
F.P.M.
bhpVt
MPH

Hub C-532D
Blades 89301-3
Std. Spinner
1500833175.51140720184685600193340510199
 
Hub C-5315S
Blades 618A
(Impregnated Wood)
Std. Spinner
1420835175.51060725182600595190235495198
 
Hub C-532D
Blades 89301-3 wth
De-icer Boots
Std. Spinner
1460860175.51100730182660595190300515197
 
Hub C-5315S
Blades 614ocl.5-12
Std. Spinner
1425835175.51070710   182.5615590   191.5260505199

For the full report see HERE


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
July 11, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-40F, A.C. No. 41-13601

Subject:      Performance Test
Section:      Flight Section
Serial No:   PHQ-M-19-1440-A

SUMMARY

A.Purpose
 
  1.Report on performance tests of P-40F airplane equipped with Packard-Merlin V-1650-1 engine and three-bladed constant speed propeller, design No. 89301-3, blade angle range 26.5° to 56.5° at 42 inch radius. Gross weight as tested 8450 pounds. Except where otherwise stated, landing gear retracted; wing flaps neutral; carburetor cold; cabin closed; cooling shutters in flush position in level flight, wide open in climb; six .50 caliber guns in place with openings taped; wing bomb shackles with sway braces installed. b.h.p. figures obtained from preliminary power charts furnished by Power Plant Laboratory.
 
B.Test Results
 
  1.High Speeds, mixture control auto-rich

 
 AltitudeTrue Speed
m.p.h.
r.p.m.b.h.p.BlowerThrottle
 
   9,800320   26501080Low  Part
 12,800350.530001240Low  Wide (Critical Alt.)
 16,700336.526501010High  Part
 19,270364.530001105High*Wide (Critical Alt.)

 *Airplane is 3.5 m.p.h. faster with mixture control adjusted for maximum power.

  4.Climb results: Throttle open to 48" Hg. manifold pressure or wide open when below 48" Hg. in both high and low blower ratios; high blower used above 13,000.

 
 AltitudeTrue Speed
m.p.h.
r.p.m.b.h.p.Rate of Climb
Ft./min.
Time of Climb
Min.
 
           01492850113521000
   5,000164285011802160  2.35
   9,600176285012402210  4.45
 13,0001852850109017806.2
 15,000191285010851860  7.25
 20,0002052850  980148010.2  
 25,000   213.52850  835100014.25
 30,0002222850  680  53021.0  
 S/C 34,000        2292850-  10037.5  
 A/C 35,500        -2850-      0-

For the full report see HERE


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
February 18, 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-40F, AAF No. 41-13635

Subject:      Propeller Tests
Section:      Flight
Serial No:   FS-M-19-1549-A

SUMMARY

A.Purpose.
 
  1.Report on performance of P-40F airplane, AAF No. 41-13635 equipped with five different propellers, each test being run with a propeller of particular blade design number, hub number, and spinner as indicated. Airplane equipped with V-1650-1 engine and flown with wing flaps neutral, wheels up, carburetor cold, mixture "auto-rich", auto boost "off", radiator flaps neutral for level flight and wide open for climbs. Configuration for all tests as follows: Six .50 caliber wing guns with ball type vent tubes in place, belly tank shackles and sway braces, but no tank installed; no ammunition in place, and full gas and oil load at take-off.
 
B.Test Results.
 
  1.High Speed at 18,100 feet altitude.

 
 PropellerTrue Airspeed
MPH
b.h.pRPM
 
 Hub C-532D
Blades 89301-3
Std. Spinner
355.011002950
 
 Hub C-532D
Blades 89306-19S
Std. Spinner
356.011002950
 
 Hub C-532D
Blades 89303-23W
Std. Spinner
353.011002950
 
 Hub C-5315 S
Blades 61401.5-21
Std. Spinner
350.511002950
 
 (Rotol) Hub RX5/3
Blades RA-675/H
Special Spinner
356.011002960

  3.Maximum rate of climb at wide open throttle and high blower, 2850 RPM.


   18,000 feet    22,000 feet    25,000 feet    28,000 feet  
PropellerR/C
F.P.M.
bhpVt
MPH
R/C
F.P.M.
bhpVt
MPH
R/C
F.P.M.
bhpVt
MPH
R/C
F.P.M.
bhpVt
MPH

Hub C-532D
Blades 89301-3
Std. Spinner
19701040201.01540910207.01220810211.0910715216.0
 
Hub C-532D
Blades 89306-19S
Std. Spinner
14601020201.01140892207.0910800211.0680702215.0
 
Hub C-532D
Blades 89303-24W
Std. Spinner
20101030200.11590905207.01270815211.0960725216.0
 
Hub C-5315 S
Blades 6141C1.5-21
Special Spinner
16301020201.01260890207.0990794212.0710700216.0
 
(Rotol) Hub RX5/3
Blades RA-675/H
Special Spinner
16201005198.51200865204.5890765209.0580665213.0

For the full report see HERE


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
April 3, 1943

MEMORANDUM REPORT ON
Single Engine Pursuit P-40F, AAF. No. 41-13635

Subject:      Propeller Test
Branch:       Flight Test
Serial No:   FS-M-19-1578-A

SUMMARY

A.Purpose.
 
  1.Report on performance of P-40-F airplane equipped with three-bladed constant speed propeller, Dwg. No. 101344-24 and standard spinner. Memorandum Report No. FS-M-1549-A lists comparative performance with five other propellers. Airplane equipped with V-1650-1 engine and flown with wing flaps neutral, wheels up, carburetor cold, mixture "auto-rich", auto boost "off", high blower ratio, radiator flap neutral for level flight and wide open for climb, full gas and oil load at take-off, six .50 caliber wing guns with ball type blast tubes in place, no ammunition, and belly tank shackles in place. Horsepower figures obtained from power charts.
 
B.Test Results.
 
  1.Level flight speeds at 18,100 feet.


Belly Tank Sway Braces Installed
(Without Tank)
Belly Sway Braces Removed.

True Speed
MPH
RPMb.h.p.True Speed
MPH
RPMb.h.p.

365.529501100374   29501100
336   2650  890342   2650  890
311   2400  760317.52400  760
283.52200  635291.52200  635
258   2000  530266   2000  530
233   2000  445240   2000  445
194   2000  360200   2000  360

  2.Maximum rate of climb at wide open throttle and high blower, 2850 RPM. Belly tank sway braces installed (without tank).


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

18,00020121851040
22,0002071725  915
25,0002121380  820
28,0002171040  710

For the full report see HERE


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
January 30, 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-40N, A.C. No. 42-9987

Subject:      Flight Tests
Section:      Flight
Serial No:   FS-M-19-1535-A

SUMMARY

A.Purpose.
 
  1.report on flight tests of Curtiss P-40N (P-40K loaded to 7413 pounds with the same drag comditions as P-40N) airplane at the manufacturer's plant. Airplane equipped with Allison V-1710-81 engine and a three-bladed 11 feet 0 inches constant speed electric propeller, balde design No. 89303-24, blade angle range 54.5° to 24.4° at 42 inch radius. Gross weight at take-off was 7413 pounds with c.g. location at 30.15 percent m.a.c., wheels up. Wheels up, wing flaps neutral, carburetor cold, mixture auto-rich, unless otherwise specified, one flame dampening stack per cylinder, four .50 caliber wing guns with blast tubes taped and 235 rounds of .50 caliber ammunution per gun. Radio and radio mast and single strand antenna in place with belly tank shackle in place. Equipped with experimental aluminum alloy radiators, Dwg. No. B22959, Serial No. 9-R, and Dwg. No. B22959, Serial No. 10-L. No rear view mirror, no external gun peep sight. 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).
 
B.Test Results.
 
  1.High speeds, cowl flaps in the neutral position.

 
 Altitude
Feet
Airspeed
MPH
RPMb.h.p.ThrottleIntake Man. Pr.
"Hg.
 
   296032330001125Part-
   296034430001415Part57
 1055034830001125Part-
 *10550  37830001480Wide57
 **17300   37130001125Wide-
 297003483000  706Wide-

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

  3.Climb data, cowl flaps open, mixture control in the autorich position. Throttle set for 57 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 Level156.5300014003520     0
   5,000168.53000145036401.39
 *8,000174   3000148037202.21
 10,000175.53000134034402.77
 15,000180.53000110526804.41

  *Critical altitude for war emergency power in climb.

  4.Climb data, cowl flaps open, mixture control in the auto-rich position, throttle set for 50.5 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 Level151300011953140     0
   5,000163300012453260  1.56
 10,000175300012903375  3.07
 *10,400 176300013003380  3.19
 15,000   180.5300010902680  4.72
 20,0001863000  9051970  6.89
 25,0001913000  7501400  9.89
 30,0001973000  625  89014.33
 35,0002033000  520  40022.52
 S/C 38,200        -3000-  10037.37
 A/C 39,200        -3000-      0-

  *Critical altitude for military power in climb.

For the full report see HERE


PROOF DEPARTMENT
ARMY AIR FORCES PROVING GROUND COMMAND
EGLIN FIELD, FLORIDA
7 June 1943

FINAL REPORT ON
TEST OF OPERATIONAL SUITABILITY OF P-40N-1 AIRPLANE

CONCLUSIONS.    It is concluded that:

              a.    In speed, maneuverability, and rate of climb up to approximately twenty thousand (20,000) feet the P-40N-1 is the best of the P-40 series tested to date. While the P-40N-1 is the superior in performance of the P-40 series, it is generally inferior to all other current types of fighters tested at this station.

              b.    The P-40N-1 is of a design which is believed to have reached its limit in performance unless major changes in control surface design, wing form, structure and horsepower are made.

              c.    The fire power of four (4) present slow firing .50 caliber machine guns is considered insufficient for the majority of combat missions where heavily armored enemy aircraft are encountered, or for most ground strafing missions.

              d.    The engine of the P-40N-1 is unsatisfactory in the following respects:

 (1)After successive flights at or above twenty-three thousand (23,000) to twenty-five thousane (25,000) feet, the engine develops progressive ignition trouble, which lowers the practical operational ceiling of the aircraft.
 
 (2)Engine operation is unsatisfactory above thirty thousand (30,000) feet at other than full throttle and nearly full R.P. M. conditions. (Believed due to caburetion.) This precludes formation flying at these altitudes.

              e.    The clear vision panel obtructs vision and is deemed unnecessary because the entire canopy may be rolled back if visibility is retricted. If there are areas where the panel is needed, it could readily be installed on the front left panel at a modification center.

              f.    Take-off time is increased due to hand cranking.

              g.    Cooling shutters can not be moved to "full closed" or "full open" position at cruising and faster speeds.

              h.    New wheel and flap indicators are satisfactory.

For the full report see HERE


ARMY AIR FORCES
MATERIEL COMMAND
Wright Field, Dayton, Ohio
14 January 1944

MEMORANDUM REPORT ON
Pursuit Single Engine P-40N-5, A.C. No. 42-105241

Subject:      Performance Tests and Range Survey
Section:      Flight
Serial No:   Eng-47-1685-A

SUMMARY

A.Purpose.
 
  1.To report results of performance tsts on the P-40N-5, AAF No. 42-105241, with additional data to calculate range and endurance under combat configurations.

 High speed at 3000 rpm, mixture auto-rich, cooler flaps set for high speed.


Altitude
Feet
Airspeed
MPH
RPMb.h.p.ThrottleGross Weight
Lb.

Sea Level287100544.5Part8300
  5000306103644.5Part8260
10000   325.5106844.5Part8220
15000344110044.5Part8180
*16400  350111044.5W.O.8170
20000   342.5  97739.2W.O.8140
25000326  79532.1W.O.8090

 *Critical altitude for 44.5 in. Hg. manifold pressure at 3000 rpm in level flight.

 Climb data at 3000 rpm, mixture auto-rich, cooler flaps set for combat climb.


Altitude
Feet
Rate of Climb
Ft/Min.
Time to Climb
Min.
True Speed
MPH
BHPManifold
Pressure "Hg.
ThrottleGross Weight
Lb.

Sea Level18600   152102044.5Part8300
  50001900  2.66166105544.5Part8260
100001935  5.27179108544.5Part8220
*14000 1960  7.32190110544.5W.O.8190
20000131011.02201  87535.4W.O.8140
25000  76015.93211  73529.8W.O.8090
S/C 31000          10033.64-----
A/C 32000             0------

 *Critical altitude for 44.5 in. Hg. manifold pressure at 3000 rpm.

 Speed-Power, Level Flight, P-40N-5 42-105241
 Climb Performance, P-40N-5 42-105241

For the full report see HERE


ENGINEERING DIVISION MEMORANDUM
REPORT SERIAL NO. ENG-47-1728-A
Wright Field, Dayton, Ohio
5 April 1944

FLIGHT TESTS ON THE CURTISS
XP-40Q-2, AAF No. 42-9987

Summary
 
        In general the airplane performance and handling characteristics were very good, and it is a decided improvement over previous models of the P-40 series. At war emergency power with water injection a high speed of 420 MPH at 15,000 ft. and a maximum rate of climb of 4410 ft. per minute at 5000 ft. were obtained. At military power a high speed of 407 MPH at 24,000 ft. and a maximum rate of climb of 3210 ft. per minute at sea level were obtained. At 3200 RPM with water injection, a maximum increase of speed of 4 MPH at 20,500 ft. and a maximum increase in the rate of climb of 530 ft. per minute at 16,700 ft. were obtained. Improved performance through use of 3200 RPM, war emergency power, may only be realized between 12,000 and 32,000 ft. in climb and between 20,000 ft. and 32,000 ft. in level flight.

 Speed vs Altitude, XP-40Q-2 42-9987
 Climb & Ceiling, XP-40Q-2 42-9987

For the full report see HERE


AEROPLANE AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
27 May 1942

Kittyhawk A.K.572
(Allison V-1710 F.3.R)
Rate of climb and position error measurements.

SUMMARY

                    The performance on climb has been measured at a weight of 8480 lb. The results show:-

The maximum rate of climb1640 ft/min at 11,400 ft.
Time to 10,000 feet.6.2 minutes
Time to 20,000 feet.14.2 minutes.
Service ceiling28,700 feet.
Estimated absolute ceiling29,900 feet.

                    The position of the pressure head, the position error correction, and the correction to the altimeter when connected to the static of the airspeed system are included in the report.

                    Kittyhawk AK572 Performance on Climb

For the full report see HERE


AEROPLANE AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
3 June 1942

Kittyhawk A.L.229
(Allison V-1710 F.3.R)
Performance tests with an external fuel tank fitted.

SUMMARY

                    Performance measurments were required on Kittyhawk A.L.229, with an external fuel tank fitted. Comparitive level speeds were also measured with the tank removed. The tests show:-

Maximum rate of climb1530 ft/min at 12,000 ft.
Time to 20,000 ft.15.0 mins.
Service ceiling27,600 ft.
Maximum level speed with tank fitted =322 m.p.h. at 14,200 ft.
Maximum level speed with tank removed =332 m.p.h. at 14,400 ft.

                    Kittyhawk A.L.229 - Performance on Climb
                    Kittyhawk A.L.229 - Level Speed Performance

For the full report see HERE


AEROPLANE AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
14 September 1942

Kittyhawk I. A.L.229
(Allison V-1710 F.3.R)
Level speed measurments with flame damping exhausts fitted.

SUMMARY

                    Level speed measurements have been made of Kittyhawk I, A.L.229, fitted with flame damping exhausts for comparison with the results obtained on the same aeroplane fitted with individual stub exhausts (reported in 10th part of Report No.A.& A.E.E./783). With flame damping exhausts the top speed is reduced by 1 to 2 m.p.h. true air speed.

Level speed with flame damping exhausts fitted.

Standard
Height in
Feet.
True airspeed
m.p.h.
A.S.I.
m.p.h.
Position
Error
Correction m.p.h.
Compressibility
Correction
m.p.h.
R.P.M.Manifold pressure
inches of Hg.
12,000322260   +9.4-1.5300041.5
14,000329257.5+9.3-1.9"41.5
   14,400 *330256.5+9.3-2.0"41.5
16,000   327.5248.5+9.0-2.1"39.0
18,000322237   +8.4-2.2"26.0

                    *   Full throttle height.

                    Kittyhawk I AL-229 - Level Speeds and Manifold Pressure at Height

For the full report see HERE


AEROPLANE AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
8 October 1942

Kittyhawk I. A.K.751
(Allison V-1710 F.3.R))

Handling and performance with a Hydulignum propeller.

SUMMARY

                    Brief performance and handling trials have been made on a Kittyhawk I fitted with a Hydulignum bladed propeller. The results of the performance trials are summarized below:

Maximum rate of climb=1350 ft/min. at 12,000 feet.
Time to reach 10,000 ft.=7.9 mins.
Time to reach 20,000 ft.=17.25
Service ceiling=28,600 feet.
Maximum true airspeed=331 m.p.h. at 14,000 feet.

                    These performance figures have been reduced on the p - basis. Compared with a standard Kittyhawk I the top speed is unchanged, but the maximum rate of climb is reduced by 290 ft/min. The ceiling is about the same.

                    The handling characteristics have deteriorated with change of propeller. There is now a marked change of directional trim with change of speed. On the climb at low airspeeds, full starboard rudder bias is necessary to fly feet off, but in the dive the aircraft has to be re-trimmed in the opposite direction. The aircraft has also to be re-trimmed in level flight for varying throttle positions. The change of trim with speed would be a serious handicap to the pilot during combat and considerably reduces the usefulness of the aircraft as a fighter. Apart from this, the general handling characteristics are similar to a normal Kittyhawk I.

                    Kittyhawk I AK751 - Rate of Climb, Time to Height, and Boost
                    Kittyhawk I AK751 - Level Speeds and Boosts at Heights

For the full report see HERE


AEROPLANE AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
15 October 1942

Kittyhawk II. F.L.220
(Merlin V-1650-1)

Climb and level speed performance and position
error.

SUMMARY

                    Climb and maximum level speed performance has been measured on Kittyhawk II. F.L.220. Briefly, the results were :-

Max. rate of climb at full throttle height M.S. gear2020 ft/min @ 10,200 ft.
Max. rate of climb at full throttle height F.S. gear1620 ft/min @ 17,000 ft.
 
Time to reach 10,000 ft.5.0 mins.
Time to reach 20,000 ft.10.9 mins.
Time to reach 30,000 ft.21.8 mins.
 
Service ceiling34,300 feet.
Estimated absolute ceiling35,400 feet.
 
Max. level true air speed in M. S. supercharger gear347 m.p.h. @ 14,700 ft.
Max. level true air speed in F. S. supercharger gear354 m.p.h. @ 20,400 ft.

                    Kittyhawk II FL-220 - Performance on Climb
                    Kittyhawk II FL-220 - Level Speed and Boost at Heights

For the full report see HERE


AIRCRAFT AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
6 June 1943

Kittyhawk IA E.T.573
(Allison V-1710 F3R)

Level speed performance
with a modified engine cowling
incorporating air cleaners.

SUMMARY

                    All-out level performance. There performance results have been corrected to standard atmposheric conditions and to 95% of the take-off weight, viz, 8,220 lb., by the methods given in Report No. A.& A.E.E./Res/170. The position error correction has been taken from that given in the 8th Part, Report A.& A.E.E./783, on Kittyhark A.K.672.

                    The full results of the all-out level speeds are given in Table I and in Fig.1. Briefly the results are:-

Standard
height
(feet)
Max
T.A.S.
m.p.h.
Boost
Ins. Hg.
  2,00029242   
10,00032242   
  13,500*33542   
20,00032032.6

                    *   Full throttle height.

                    Kittyhawk IA ET573 - Level Speed Performance with Air Cleaner Cowling Fitted

For the full report see HERE


AIRCRAFT AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN
20 June 1943

Kittyhawk IA E.T.573
(Allison V-1710 F3R)

Level speed performance
with normal cowling fitted.

SUMMARY

                    The results of the tests have been corrected to standard atmospheric conditions and to 95% of the take-off weight, viz. 8,220 lb., by the methods given in Report AAEE/Res/170. In evaluating these speeds the same position error correction has been used as for the previous tests on this aircraft, viz. that measured on A.K.572 and given in the 8th Part of Report No. AAEE/783.

                    The results of these tests are given fully in Table I and Fig. 1, and summarised below:-

Maximum level speed at 10,000 ft. 329 mph. TAS.
Maximum level speed at 13,800 ft. 344 mph. TAS.
Maximum level speed at 20,000 ft. 330 mph. TAS.

                    The results obtained with the tropical cowling fitted have been extracted from the 18th Part of this Report and plotted in Fig. 1 for comparison

                    Kittyhawk IA ET573 - All Out Level Speed Performance

For the full report see HERE


R.A.A.F. H.Q.
No. 1 AIRCRAFT PERFORMANCE UNIT
LAVERTON
22 August 1944

BRIEF PERFORMANCE TRIALS OF P-40N AIRCRAFT
(Allison V-1710 - 81)

PART 1. - P-40N - 5CU

SUMMARY

                    The performance of the subject aircraft is summarised as follows:-

I.C.A.N.
Altitude
Feet
R.P.M.
No.
A.M.P.
in. Hg.
Maximum
Speeds
mph.
Time to
Altitude
minutes
Rate of Climb
Ft/minute
Military Rated Power
0300043.827302220
10000300043.83104.42310
15000300043.83287.31960
    16200 *300043.8332--
200003000    37.1xx3249.91460
275003000    28.2xx294--
300003000--21.6440
Normal Rated Power
0260039.026602060
10000260039.03004.82130
15000260039.03187.71960
    15200 *260039.0318--
200002600    32.3xx30910.31460
275002600    24.5xx283--
300002600"-22.0440

                    *..... denotes Critical Full Throttle Height
                  xx..... denotes Level speeds only
                    Service Ceiling - 33500 feet.

                    P40N-5CU A29-418 Climbing Trials - Military Power
                    P40N-5CU A29-418 Climbing Trials - Rated Power
                    P40N-5CU A29-418 Speed Trials

PART 11. - P-40N - 1CU

SUMMARY

                    The performance of the subject aircraft is summarised as follows:-

I.C.A.N.
Altitude
Feet
R.P.M.
No.
A.M.P.
in. Hg.
Maximum
Speeds
mph.
Time to
Altitude
minutes
Rate of Climb
Ft/minute
Military Rated Power
Sea Level300043.82870.02300
  5000300043.83032.02360
10000300043.83214.12410
x 14000   3000 43.8-5.82450
150003000F.T. or 43.83396.22335
x 17000   3000F.T. or 43.83467.1-
200003000F.T.3408.51750
250003000F.T.32812.21160
300003000F.T.30718.2575
Normal Rated Power
Sea Level260039.02740.01940
  5000260039.02912.52000
10000260039.03075.02065
x 13800   260039.0-6.82095
150002600F.T. or 39.03247.41980
x 16100   2600F.T. or 39.03278.1-
200002600F.T.32210.41440
250002600F.T.31014.8895
300002600F.T.29823.4355

                    x..... denotes Critical Full Throttle Height
                    Service Ceiling - Undetermined.

                    P40N-1CU A29-412 Climb Performance

WAR EMERGENCY RATED POWER PERFORMANCE

CLIMB PERFORMANCE
 
WEIGHT 7900 LBS.
TABLE 1.
 

I.C.A.N.
Altitude
Feet
A.S.I.
mph
R.P.M.
No.
A.M.P.
ins. Hg.
Rate of
Climb
Ft/min.
Time
from Start
min.
WAR EMERGENCY RATING
Sea Level150300057.0  31000
  1000150300057.0  31400.3
  2000150300057.0  31800.6
  3000150300057.0  3220  0.95
  5000150300057.0  3300  1.55
x 6800 150300057.0  33702.1
  7500150300055.5  32702.3
10000150300050.5  29303.1
12500147300046.2526104.0
15000145300042.2523005.0

                    x..... denotes Critical Full Throttle Height

LEVEL SPEEDS
 
WEIGHT 7900 LBS.
TABLE 2.
 

I.C.A.N.
Height
Feet
T.A.S.
mph
R.P.M.
No.
Boost
in Hg.
WAR EMERGENCY RATING
Sea Level314300057.0  
  5000335300057.0  
x 9200352300057.0  
10000352300055.25
15000348300046.75

                    x..... denotes Critical Full Throttle Height

                    P40N-1CU A29-412 Climb Performance W. E. Power Rating
                    P40N-1CU A29-412 Level Speed Performance W. E. Power Rating

For the full report see HERE


(Click to enlarge)
 
(Click to enlarge)
 
(Click to enlarge)
 
(Click to enlarge)
 

Supplemental

Memorandum Report on XP-40, A.C. No. 38-10: Results of Comparitive Speed Tests
Memorandum Report on XP-40, A.C. No. 38-10: Flush Mounted Static Tube
Memorandum Report on XP-40, A.C. No. 38-10: Speed Test with Retractable Type Jet Propulsion Exhaust Stacks
Memorandum Report on P-40, A.C. No. 39-156: Speed Tests of P-40 Airplane
Memorandum Report on P-40C, A.C. No. 41-13377: Test of Carburetor Air Filter
Memorandum Report on P-40E, A.A.F. No. 40-633: Experimental Air Filter
Memorandum Report on P-40E, A.A.F. No. 40-633: Spin tests
Memorandum Report on P-40E, A.C. No. 40-405: High Speed and Time to Climb to 15,000 ft.
Memorandum Report on P-40F, A.C. 41-13601: Cruising Speeds with 75 Gal. Belly Tank.
Memorandum Report on P-40K-1, A.A.F. No. 42-9761: Speed Tests
Memorandum Report on P-40Q, AAF No. 42-9987: Pilot's Comments
Performance Data, Pursuit Airplanes, July 24, 1941.
Memorandum Report on Pursuit (Various Types), October 13, 1941.
P-40 Official Summary of Characteristics
Performance Chart, Curtiss P-40. Based on Official Performance Summary
P-40B Official Summary of Characteristics
P-40B Official Performance Summary
P-40E Official Summary of Characteristics
P-40E Official Performance Summary
P-40E Specifications and Performance, 16 June 1943
P-40F Specifications and Performance, 16 June 1943
P-40, P-40B, P-40C Specific Operating Instructions
P-40D Operation Instructions
P-40E Operation Instructions
Kittyhawk II Flying and Engine Limitations, 6/8/42
Performance figures for Kittyhawk II, British Air Commision, 9.9.42
Service Use of High Power Outputs on Allison V-1710 Engines

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