P-39 Performance Tests

WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
February 5, 1941

MEMORANDUM REPORT ON
Pursuit One-Engine YP-39, A.C. No. 40-30

Subject:      Acceptance Performance Test
Section:      Flying Branch
Serial No:   PHQ-M-19-1185-A

Summary

A.Purpose
 
  1.Report on tests conducted at the manufacturer's plant on Bell YP-39. Airplane equipped with Allison V-1710-37 engine and 3-bladed constant speed propeller, blade design No. 614CC1.5-21, blade angle range 21° to 51° at 42" radius. Gross weight as tested 6592 lbs., c.g. location wheels down 26.1% m.a.c.; radio antenna in place; propeller not equipped with cuffs; two exhaust stacks per cylinder; venturi tube for alternate source of gyro suction retracted; wheels up, wing flaps neutral, carburetor cold, mixture control in automatic rich position, prestone and oil cooler shutters set flush with cowling during level flight, wide open in climb except where otherwise stated; guns in place.
 
B.Test Results
 
  1.High Speed at critical altitude for military rated power is 368 mph at 1090 bhp at 3000 rpm at 13,600 ft. The high speed is the same with or without camouflage. The camouflage consisted of one primer coat of zinc chromate and two coats of dull lacquer.
 
 2.High speed at critical altitude for normal rated power is 348 mph at 940 bhp at 2600 rpm at 13,000 ft.
 
 3.Speed with prestone and oil cooler shutters closed at 5000 ft. at 960 bhp at 2600 rpm is 329 mph.
 
 4. Cruising data at 13,000 ft.:

 
 Speed
MPH
R.P.M.B.H.P.% Normal
Rated Power
 
 308228072075   
 296221062064.6
 278212052554.7
 246192041543.2
 202172031033.5

 5.Climb data:

 
 AltitudeTrue Speed
MPH
R.P.M.B.H.P.Rate of climb
Ft/Min
Time of Climb
Min.
 
 S.L.1533000109036000   
   5,0001663000109036001.4
 10,0001793000109036002.8
 13,6001883000  99034103.8
 15,0001912600  83522604.6
 20,0002012600  68515807.3
 25,0002112600  550  98011.2  
 30,0002202600  430  44018.7  
 S/C 33,300       2262600-  10032.4  
 A/C 34,400       2272600-      0-

For the full report see HERE

See also: Memorandum Report on YP-39 A.C. No. 40-30, Tests Conducted at Manufacturer's Plant


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
July 17, 1941

MEMORANDUM REPORT ON
Pursuit Single Engine P-39C, A.C. No. 40-2988

Subject:      Flight Tests
Section:      Flying Branch
Serial No:   PHQ-M-19-1266-A

Summary

A.Purpose
 
  1.Report on flight tests of Bell P-39C. Airplane equipped with Allison V-1710-35 engine and 3-bladed constant speed propeller, blade design No. 614CC1.5-21, blades not equipped with cuffs. Gross weight as tested 6689 lbs. Wheels up; wing flaps neutral; carburetor cold; one exhaust stack per cylinder; airplane camouflaged; cannon, two 30 cal. and two 50 cal. guns as well as radio antenna in place. Horsepowers were obtained from Fig 3, T.O. No. 02-5AD-1.
 
B.Test Results
 
  1.Military rated power speeds:

 
 Altitude
Ft.
Speed
MPH
R.P.M.B.H.P. Oil Cooler and Prestone
Flap Control Position
 
   13,05036930001150        Wide open
 *16,10037930001150        Flush with cowling
     5,000   340.530001150        Wide open
     5,00035030001150        Flush with cowling

 *Critical altitude for military rated power in level flight.

  3.Climb data, prestone and oil cooler flaps wide open, mixture control automatic rich below 18,000 ft., automatic lean position above 18,000 ft. Oil and prestone temperatures do not meet Air Corps requirements in climb.

 
 Altitude
Ft.
Speed
MPH
R.P.M.B.H.P.Rate of climb
Ft/Min
Time of Climb
Min.
 
 S.L.1533000115037200
   5,000165300011503720  1.35
 10,0001783000115037202.7
 13,050   185.53000103030403.6
 16,750   194.53000  89523605.0
 20,0002002600  67515306.9
 25,0002112600  535  97511.0  
 30,0002212600-  44018.4  
 S/C 33,200       2272600-  10032.2  
 A/C 34,150       2292600-      0-

For the full report see HERE

See also Bell Aircraft chart of P-39C performance


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
December 3, 1941

MEMORANDUM REPORT ON
Pursuit Single Engine P-39D, A.C. No. 41-6722

Subject:      Flight Tests
Section:      Flying Branch
Serial No:   PHQ-M-19-1325-A

Summary

A.Purpose
 
  1.To report on flight tests of Bell P-39D airplane, A.C. No. 41-6722. Airplane equipped with Allison V-1710-35 engine and 3-bladed constant speed propeller, blade design No. 614-1C1.5-21, blade angle range 51.5° to 21.5° at 42 inch radius. Gross weight as tested was 7525 lbs.; c.g., wheels up, located at 25.8% m.a.c.; wheels up; wing flaps neutral; oil cooler and prestone shutters flush, and carburetor cold unless otherwise specified. Airplane camouflaged, radio antenna in place, cannon and two .50 cal. guns in nose and four .30 cal. guns in wings. Horse powers obtained from page 12 of Specification No. 123-E. Individual intake port backfire screens not installed in engine.
 
B.Test Results
 
  1.Speeds in level flight:

 
 Altitude
Ft.
Speed
MPH
R.P.M.B.H.P.Throttle
Position
Mixture
Setting
 
   5,18033630001150PartBest power
 *13,100     347.526001000Wide openBest power
 **13,800    36830001150Wide openBest power
 13,80036530001125Wide openAuto rich
 25,3003523000  740Wide openBest power
 25,3003473000  710Wide openAuto lean
 25,3003453000  695Wide openAuto rich

   *Critical altitude for normal rated power in level flight.
 **Critical altitude for military rated power in level flight.

  3.Climb data: Prestone and oil cooler shutter wide open; mixture control auto rich below 20,000 ft.; auto lean above 20,000 ft.

 
 Altitude
Ft.
Speed
MPH
R.P.M.B.H.P.Rate of
climb Ft/Min
Time of
climb Min.
 
           01573000115027200   
   5,000169300011502720  1.84
 10,000183300011502720  3.68
 *12,400  190300011502720  4.56
 13,6501923000108025155.0
 15,0001942600  86518805.7
 20,0002032600  71013008.9
 25,0002132600  585  80013.8  
 30,0002252600  465  30020.8  
 S/C 31,100       2292600  415  10032.0  
 A/C 33,200       2322600  390      0-

 **Critical altitude for military rated power in climb.

For the full report see HERE

P-39D data taken from this report was used in the chart - Compartive Performance of P-39D, P-40F, and P-51 Airplanes


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
May 22, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-39D, A.C. No. 41-6897

Subject:      Report of Flight Tests
Section:      Flight Section
Serial No:   PHQ-M-19-1385-A (Addendum No. 1)

Summary

A.Purpose
 
  1.To report correction to Memorandum Report, Serial No. PHQ-M-19-1385-A. This report replaces the original which should be destroyed.
 
  2.To report on flight tests of Bell P-39D airplane, A.C. No. 41-6897. Airplane equipped with Allison V-1710-35 engine and three-bladed constant speed propeller, blade design No. 614-1cl.5-21 blade angle range 51.5° to 21.5° at 42 inch radius. Airplane loaded to an approximate weight of 7800 pounds not including a 75 gallon belly tank installation. Wheels up; wing flaps neutral; oil cooler and prestone shutters flush and carburetor cold. Four .30 caliber wing guns, two .50 caliber synchronized guns and one cannon. Gun barrels and openings taped. Airplane as tested was fitted with winterized equipment. Horsepowers obtained from power curve dated March 25, 1941. Engine was equipped with manifold T-type screens, individual intake port screens removed.
 
B.Test Results
 
  1.Speeds in level flight at 13,000 feet.

 
 Belly Tank
Brackets &
Shackles
Removed MPH
Belly Tank
Removed
Shackles &
Brackets
in Place MPH
Belly Tank (Full)
Shackles & Brackets
in Place MPH
RPMChart
BHP
Throttle
Position
Mixture setting
 
 358--30001170W.O.A.R.
    336.5328-2600974W.O.A.R.
 -349-30001165W.O.A.R.
 --   311.530001145W.O.A.R.
 --   294.52600  967W.O.A.R.
    321.5   312.52822280  850PartA.L.
 3012922642200  700PartA.L.
 2762672412100  550PartA.L.
 2572472211900  450PartA.L.
 2222121841700  330PartA.L.

For the full report see HERE

See also:P-39D-1 Performance Chart
 Memorandum Report Serial No. PHQ-M-19-1385-A


WAR DEPARTMENT
Army Air Forces MATERIEL DIVISION
Wright Field, Dayton, Ohio
December 18, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-39D-1, A.C. No. 41-28378

Subject:      Critical Altitude and High Speed with two types of Intake Manifolds
Section:      Flight
Serial No:   FS-M-19-1521-A

Summary

A.Purpose
 
  1.To report results of flight tests on the P-39D-1 airplane. A.C. No. 41-28378, to determine the high speed and critical altitude with the streamlined manifold consisting of "T" manifolds, Dwg. No. DRIMI-42790, pipe manifolds, Dwg. DRW-L-42791, and port manifolds, Dwg. Nos. 36086 and 36085; and also with the standard manifold with "T" screens installed consisting of "T" manifolds, Dwg. No. 40041, pipe manifolds, Dwg. No. 34167, and port manifolds, Dwg. Nos. 36086 and 36085. Airplane equipped with Allison V-1750-35 engine and with three-bladed constant speed propeller, Dwg. No. 614-1cl.5-21. Gross weight as reported by the Aircraft Laboratory was approximately 7450 pounds, at 30.9 percent m.a.c., wheels up. All tests with a 20 mm cannon in nose, two .50 caliber guns in the fuselage and four .50 caliber guns in the wings, radio antenna in place, and no sway braces installed.

Power data obtained from Allison power curve for V-1710-69, 73, 35, and 39 engines dated September 29, 1942, for all tests with the streamlined manifold; power data for tests with the manifold with "T" screens was obtained from Allison curve for the V-1710-35 and 39 engines dated December 12, 1941.

 
B.Test Results
 
  1.High speed at 12,750 feet at 2970 RPM at wide open throttle.

 
 Intake
Manifold
True Speed
MPH
Manifold Pressure
"Hg.
b.h.p.
from Chart
 
 Streamlined manifold        37045.91162
 Manifold with "T" Screens36945.41172

For the full report see HERE


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
November 25, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-39M-3, A.C. No. 42-4706

Subject:      Flight Tests
Section:      Flight
Serial No:   FS-M-19-1511-A

Summary

A.Purpose
 
  1.Report on flight tests of Bell P-39M-3 airplane at the manufacturer's plant. Airplane equipped with Allison V-1710-83 engine and a three-bladed Curtiss Electric constant speed propeller, blade design No. 614-10-1-5-21, blade angle range 26° tp 56° at 42 inch radius. Gross weight at take-off was 7430 pounds with c.g. at 28.6 percent m.a.c., wheels up. Landing gear retracted; wing flaps neutral; carburetor cold; mixture auto-rich unless otherwise specified; one 37 mm cannon, four .30 caliber wing guns, and two .50 caliber nose guns in place with a corresponding ammunition load of thirty rounds of 37 ammunition, three-hundred rounds of .30 caliber ammunition per gun, and two-hundred round of .50 caliber ammunition per gun; radio, type 522, and radio mast which acts as a antenna wire in place, antenna removed; belly tank shackle and sway bracing in place; blast tube openings covered with tape. Horsepowers obtained from power curve V-1710-83 and -85 dated September 19, 1942 (2:1 propeller gear ratio; 9.6:1 blower gear).
 
B.Test Results
 
  1.High speeds, oil cooler shutters in flush position.

 
 Altitude
Feet
Speed
MPH
RPMb.h.p.Prestone Shutter Pos.
(Turns from W.O.)
Test Condition
 
 *15,900  373300011256Military Rated Power
 ** 9,500      385.5300014206War Emergency Power
   9,500350300011256Military Rated Power
   2,750345300013306Throttle open to 57" Hg. Man. Press.
   2,750322300011256Military Rated Power
 30,2003373000  6359Throttle wide open at military rated RPM.

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

  5.Climb data: Prestone and oil cooler shutters wide open; mixture control in the auto-rich position. Throttle set for 50.5" Hg. at 3000 RPM or wide open when below.

 
 Altitude
Feet
Speed
MPH
RPMb.h.p.Rate of Climb
Ft./Min.
Time of Climb
Min.
 
 S.L.1543000118528700   
   5,000167300012103120  1.67
   9,900180300012503320  3.19
 15,000188*10402640  4.91
 20,000193*  8802000  7.09
 25,000198*  725140010.08
 30,000203*  595  80014.76
 35,000208*-  20026.09
 S/C 35,900       -*-  10032.09
 A/C 36,700       -*---

  6.Climb data: Prestone and oil cooler shutters wide open; mixture control in the auto-rich position. Throttle set for 57" Hg. at 3000 RPM or wide open when below.

 
 Altitude
Feet
Speed
MPH
RPMb.h.p.Rate of Climb
Ft./Min.
Time of Climb
Min.
 
 S.L.1603000135537400   
   5,000   173.53000139538401.32
   6,5001773000140038801.71
 10,0001843000125033102.69
 15,000   189.5-103026404.38

For the full report see HERE


WAR DEPARTMENT
AIR CORPS, MATERIEL DIVISION
Wright Field, Dayton, Ohio
October 17, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-39N-1, A.C. No. 42-4400

Subject:      Flight Tests
Section:      Flight
Serial No:   FS-M-19-1487-A

Summary

A.Purpose
 
  1.Report on flight tests of Bell P-39N-1 airplane at the manuacturer's plant. Airplane equipped with Allison V-1710-85 engine and three-bladed constant speed aero-propeller, blade design No. A-20-156-17, blade angle range 28° to 63°, at 42 inch radius. Gross Weight at take-off was 7274 pounds with c.g. at 29.0 percent, wheels up. Wheels up; wing flaps neutral; carburetor cold; mixture auto-rich unless otherwise specified; one exhaust stack per cylinder; one 37 mm. cannon, four .30 caliber wing guns, and two .50 caliber nose guns in place with a corresponding ammunition load of thirty rounds of 37 mm. ammunition, 300 rounds of .30 caliber ammunition per gun, and 250 rounds of .50 caliber ammunition per gun. Radios and radio mast and antenna in place with belly tank shackle without sway bracing in place.

Horsepowers obtained from power curve V-1710-83 and 85 dated September 19, 1942 (2.23:1 propeller gear ratio; 9.6:1 blower gear).

 
B.Test Results
 
  1.High Speeds, blast tubes closed.

 
 AltitudeSpeed
MPH
RPMb.h.p.Man.Pr.
Hg.
Oil Cooler
Shutter
Position
Prestone
Shutter
Position
 
 *16,100389.53000112546.7Flush6 turns from W.O.
 **9,700398.53000142059.8Flush6 turns from W.O.
     2,700358.03000133057.0Flush6 turns from W.O.
   30,100353.0300065526.7Flush6 turns from W.O.

 Airplane does not meet Air Corps cooling requirements at any of these powers.

Test with blast tubes open showed no measurable difference in speed from test with blast tubes closed.

*Critical altitude for military rated power in level flight.
**High speed at critical altitude for war emergency power; critical altitude for 57" Hg. was 10,900 feet. Speed at wide open throttle at 10,900 feet was 1.5 MPH less than speed at 9700 feet.

  3.Climb data, prestone and oil cooler flaps wide open; blast tubes closed; mixture control in auto-rich position. Throttle set for 50.5" Hg. at 3000 RPM of wide open when below.

 
  
Altitude
Ft.
 
Speed
MPH
RPMb.h.p.Rate of Climb
Ft/Min.
Time of Climb
Min.
 
 S.L.1563000117033200
   5,000169300012003600  1.45
 10,000182300012303865  2.79
 11,000185300012353920  3.05
 15,000194300010603340  4.15
 20,0002053000  8852630  5.83
 25,0002163000  7451940  8.04
 30,0002273000  630126011.21
 35,0002413000--  58016.88
 S/C 38,500       --3000--  10029.2  
 A/C 39,400       --3000------

 Prestone temperature does not meet Air Corps requirements in climb. High prestone temperature observed in climb was 136°C at 11,000 feet at 1235 b.h.p. with a free air temperature of +4°C.

For the full report see HERE

See also: P-39N Level Speeds


ARMY AIR FORCES
MATERIEL CENTER
Wright Field, Dayton, Ohio
November 24, 1942

MEMORANDUM REPORT ON
Pursuit Single Engine P-39N-1, A.C. No. 42-4400

Subject:      Flight Tests
Section:      Flight
Serial No:   FS-M-19-1510-A
Summary

A.Purpose
 
  1.Report on climb and take-off tests of Bell P-39N-1 airplane at the manuacturer's plant. Airplane equipped with Allison V-1710-85 engine and three-bladed constant speed propeller, blade design No. A-20-156-17, blade angle range 28° to 63°, at 42 inch radius. Gross Weight at take-off was 7301 pounds with c.g. at 28.8 percent, wheels up. Landing gear retracted; wing flaps neutral; carburetor cold; mixture auto-rich; one 37 mm. cannon, four .30 caliber wing guns, and two .50 caliber nose guns in place with a corresponding ammunition load of 30 rounds of 37 mm. ammunition, 300 rounds of .30 caliber ammunition per gun, and 200 rounds of .50 caliber ammunition per gun. Radio and radio mast and antenna in place with belly tank shackle without sway bracing in place. Horsepowers obtained from power curve V-1710-83 and -85 dated September 19, 1942 (2.23:1 propeller gear ratio; 9.6:1 blower gear).
 
B.Test Results
 
  1.Climb data: Prestone and oil cooler flaps wide open; blast tubes closed; mixture control in the automatic rich position. Throttle set for 57 inches Hg. at 3000 RPM or wide open when below.

 
  
Altitude
Ft.
 
Speed
MPH
RPMb.h.p.Rate of Climb
Ft/Min.
Time of Climb
Min.
 
 S.L.1603000135539800
   5,0001733000137542401.22
   7,500   178.53000139043601.80
 10,0001833000126539002.41
 15,0001923000106032303.82

 Prestone temperature does not meet Air Corps requirements in climb. Highest observed prestone temperature in climb was 126°C 1t 12,000 feet at 1225 b.h.p. with a free air temperature of -12°C. Anticipated prestone oil temperature for Air Corps "hot day" 152°C.

For the full report see HERE


ARMY AIR FORCES
MATERIEL COMMAND
Wright Field, Dayton, Ohio
4 August 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-39Q-5, AAF No. 42-19615

Subject:      Flight Tests
Section:      Flight
Serial No:   ENG-47-1631-A
Summary

A.Purpose
 
  1.To report on flight tests of the Bell P-39Q-5 airplane, AAF No. 42-19615 at Wright Field.
 
B.Factual Data and Test Results
 
    High Speed in Level Flight:

               Throttle open to 57" Hg at 3000 RPM or wide open when below. Oil shutters in flush position. Coolant shutters open to 2.9 inches of gap from flush position, corresponding to approximately 6 turns from wide open, on all tests runs. The dashed line on the speed versus altitude curve on page A-1 represents the true speed that would be obtained if the coolant shutters were closed down to give a limiting standard coolant temperature of 125° C.


Altitude
Ft.
Speed
MPH
BHP
from
Chart
Manifold
Pressure
"Hg.
Test Coolant Shutter
Position
Inches open from Flush
Coolant Shutter
position to give 125°C
STD limiting temp.
In. open from flush
Corresponding
speed MPH

         0329135557   2.91.8330
  5,000352138057   2.92.2352
*10,000  374140557   2.92.6374
15,000371114046.72.91.8372
20,000366  94038.62.91.2368
25,000358  77231.72.90.5361
30,000346  62025.42.90.0350

            * Critical altitude War Emergency Power 57" Hg at 3000 RPM

            Climb data: Throttle set for 57" Hg at 3000 RPM or wide open when below. Oil shutters and colland shutters wide open.


Altitude
Ft.
Speed
MPH
BHP
from
Chart
Manifold
Pressure
"Hg.
Rate of
Climb
Ft/Min.
Time to
Climb
Min.

0172136057   36900.0
  5,000185138257   3770  1.25
*7,400191140057   3805  1.90
10,000194126051.33475  2.61
15,000199105042.82840  4.20
20,000202  88236.02200  6.20
25,000206  74030.21570  8.90
30,000208  60924.9  94012.95
35,000---  31021.8  
S/C 36,000       ---  10028.5  
A/C 37,400       -----

            * Critical altitude in War Emergency Power, Climb - 57" Hg at 3000 RPM

For the full report see HERE


ARMY AIR FORCES
MATERIEL COMMAND
Wright Field, Dayton, Ohio
9 October 1943

MEMORANDUM REPORT ON
Pursuit Single Engine P-39Q-5, AAF No. 42-19615

Subject:      Flight Tests
Section:      Flight
Serial No:   ENG-47-1651-A

Summary

            High speed at 11,000 feet (critical altitude for P39N with 57 inches manifold pressure and 3000 R.P.M.)

            Wide open throttle and 3000 R.P.M., oil shutters in the flush position. Coolant shutters open to 2.9 inches of gap from the flush position corresponding to approximately six turns from wide open.


Altitude
Ft.
Speed
MPH
BHP
from
Chart
Manifold
Pressure
"Hg.
Test Coolant Shutter
Position
Inches open from Flush

11,000385.0134054.52.9

            Performance previously obtained, with the two external caliber .50 wing guns and the airplane at the same weight, gave the following results.


Altitude
Ft.
Speed
MPH
BHP
from
Chart
Manifold
Pressure
"Hg.
Test Coolant Shutter
Position
Inches open from Flush

11,000372.5134054.52.9

            Climb Data: Wide open throttle and 3000 R.P. M., oil shutters and coolant shutters wide open.


Altitude
Ft.
Speed
MPH
BHP
from
Chart
Manifold
Pressure
"Hg.
Rate of
Climb
Ft/Min.
Time to
Climb
Min.

0171131055.034700
  5,000185133055.03540  1.43
* 8,100  191135055.03580  2.29
10,000193125551.23307  2.85
15,000197104042.62640  4.54
20,000200  87035.52007  6.71
25,000203  72029.31365  9.72
30,000206  58024.0  72514.66
S/C 34,900       208  45019.2  10029.6  
A/C 35,700       -- -- -- 0--

* Critical altitude in climb for 55 inches Hg. at 3000 R.P.M.

            The above results should not be directly compared with the results in previous climbs with two external guns in place.

            Considerable engine trouble was experienced while attempting to obtain climbs with the guns off and as can be seen from the above results, the engine was not developing full emergency power.

            Flight test made on the XP-63 airplane with two externally mounted wing guns on and off indicate that an increase of only approximately 110 Ft./Min. in rate of climb is obtained by removing the guns. Such a figure is close to the limites of climb determination accuracy. Since the wing gun installation on the P-39Q-5 is similar to that on the XP-63, it is probable that the removal of the wing guns on the P-39Q-5 has no greater effect than that determined for the XP-63.

P-39Q-5 No. 42-19615 Climb Data
P-39Q-5 No. 42-19615 Level Flight Data

For the full report see HERE


ARMY AIR FORCES
MATERIEL COMMAND
Wright Field, Dayton, Ohio
28 July 1944

MEMORANDUM REPORT ON
P-39Q Airplane, AAF No. 44-3455

Subject:      Report of Spin Tests
Section:      Flight
Serial No:   ENG-47-1779-A

Conclusions

1.   The P-39 should not be spun intentionally under any circumstances.

2.   The P-39 should not be snap rolled as the roll usually ends in a spin.

3.   The best spin recovery is to simultaneously apply opposite rudder and neutralize the stick.

4.   Power should be cut immediately if a power on spin is entered.

5.   Care must be excercised during the recovery to prevent an accelerated stall and re-enty into the spin.

6.   The wing tip spin chute does not aid recovery of the P-39Q from a flat spin.

For the full report see HERE


AEROPLANE AND ARMAMENT EXPERIMENTAL ESTABLISHMENT
BOSCOMBE DOWN

Airacobras A.H.573 and A.H.701
(Allison V-1710-EA)
Climb and level speed performance

25 September 1942

Summary

                    Performance trials have been made on Airacobras A.H.573 and A.H.701 each fitted with an Allison
V-1710.E.4. engine.

                    The results were:-

Maximum rate of climb2040 ft/min at 10,300 ft.
Service ceiling29,000 ft.
Time to 10,000 ft.  5.1 mins.
Time to 20,000 ft.11.7 mins.
Maximum true air speed in level flight355 m.p.h. at 13,000 ft.

                    Airacobra AH-573 - Rate of Climb, Boost, and Time to Height
                    Airabobra AH-701 - Level Speeds and Boost at Height

For the full report see HERE


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Supplemental

Memorandum Report on XP-39B 38-326, Comparitive Speed Tests
Memorandum Report on P-39C 40-2974, Flight Test for Determination of Fuel Consumption Data
Memorandum Report on P-39C 40-2676, Propeller Tests
Memorandum Report on P-39C 40-2990, Flight Tests - Critical Altitude and High Speed
Memorandum Report on P-39D 41-6897, Report of Flight Tests
Memorandum Report on P-39D 41-6897, Effect of Extended Landing Light
Memorandum Report on P-39D 41-6722, Carburetor Air Heater
Memorandum Report on P-39D 41-6722, Full Range Mixture Control Valve
Memorandum Report on P-39D 41-6926, Intake Manifold without back-fire screens
Memorandum Report on P-39F 41-7246, Flight Tests
Memorandum Report on XP-39E 41-19502, Flight Tests
Memorandum Report on XP-39E 41-19502, Pilot's Comments
Memorandum Report on P-39N-1 42-9337, Speed Tests, smoothed camouflage finish
P-39N Level Speeds
P-39M Performance and Specifications
Measurements of the Flying Qualities of a Bell P-39D-1 Airplane (A.A.F. No. 41-28378)
Pilot's Flight Operating Instructions for Army Models P-39K-1 and P-39L-1 Airplanes
Pilot's Flight Operating Instructions for Army Model P-39Q-1 Airplane
The High-Speed Longitudinal Stability and Control of the P-39N-1 Airplane
Airacobra A.H.573 Perliminary Handling Trails
Comparative Performance of P-39D, P-40F, and P-51 Airplanes
Airplane Performance Characteristics for the P-39 Planes

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