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 |
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 | ||||
1020 | 2600 | W.O. | 335 | 332 | 330 | |
900 | 2600 | Part | 320 | 318 | 315 | |
800 | 2600 | Part | 306 | 305 | 302 |
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 |
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 | |
1020 | 2600 | 335 | |
900 | 2600 | 320 | |
800 | 2600 | 307 |
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 |
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 |
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 | |
950 | 335 | 329 | 6.0 | |
900 | 329 | 323.5 | 5.5 | |
800 | 314.5 | 310 | 4.5 | |
700 | 298.0 | 294 | 4.0 |
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 |
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 MPH | R.P.M. | B.H.P. | % Rated BHP | |
310 | 2280 | 720 | 75 | |
286 | 2200 | 600 | 62.5 | |
258 | 2100 | 480 | 50 | |
236 | 2000 | 400 | 41.7 |
Climb data, radiator shutters wide open: |
Altitude Ft. | Rate of Climb Ft/Min | R.P.M. | B.H.P. | True Airspeed MPH | Time Min. | |
0 | 2900 | 3000 | 952 | 143 | 0 | |
5,000 | 2985 | 3000 | 1002 | 155 | 1.7 | |
10,000 | 3070 | 3000 | 1050 | 167 | 3.35 | |
14,750 | 2610 | 3000 | 955 | 176 | 5 | |
15,000 | 2160 | 2600 | 835 | 176 | 5.11 | |
20,000 | 1520 | 2600 | 700 | 183 | 7.9 | |
25,000 | 935 | 2600 | 585 | 189 | 12.0 | |
30,000 | 360 | 2600 | 490 | 195 | 20.3 | |
32,400 | 100 | 2600 | - | - | 32.0 | |
33,300 | 0 | 2600 | - | - | - |
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 |
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 | |
*5,175 | 326 | 3000 | 1150 | Part | |
*15,175 | 354 | 3000 | 1085 | Wide | |
15,175 | 335 | 2600 | 910 | Wide | |
15,175 | 307.5 | 2280 | 725 | Wide | |
15,175 | 290 | 2200 | 635 | Part | |
15,175 | 265 | 2100 | 530 | Part | |
15,175 | 239 | 1900 | 420 | Part | |
15,175 | 209 | 1700 | 300 | Part |
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. | |
0 | 140 | 3000 | 1150 | 2580 | 0 | |
5 | 151 | 3000 | 1150 | 2580 | 1.94 | |
10,000 | 162 | 3000 | 1150 | 2580 | 3.88 | |
12,850 | 162 | 3000 | 1080 | 2355 | 5.0 | |
15,000 | 172.5 | 2600 | 840 | 1600 | 6.36 | |
20,000 | 182 | 2600 | 690 | 1120 | 10.0 | |
25,000 | 190.5 | 2600 | 560 | 635 | 15.9 | |
S/C 30,600 | 199.5 | 2600 | - | 100 | 35.0 | |
A/C 31,600 | 201 | 2600 | - | 0 | - |
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 |
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 | |
11,400 | 342 | 3000 | 1150 | Wide | Belly tank removed | |
15,300 | 340 | 3000 | 990 | Wide | Belly tank removed | |
15,300 | 319 | 3000 | 965 | Wide | Belly tank installed | |
15,300 | 316 | 2600 | 820 | Wide | Belly tank removed | |
15,300 | 298 | 2600 | 800 | Wide | Belly 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. | |
0 | 146 | 3000 | 1020 | 2100 | 0 | |
5,000 | 158.5 | 3000 | 1070 | 2260 | 2.3 | |
10,000 | 170.5 | 3000 | 1120 | 2400 | 4.44 | |
11,300 | 173.5 | 3000 | 1065 | 2250 | 5.0 | |
15,000 | 177.5 | 2600 | 795 | 1370 | 7.38 | |
20,000 | 187 | 2600 | 655 | 880 | 11.82 | |
25,000 | 196.5 | 2600 | 555 | 480 | 19.42 | |
S/C 30,000 | 205 | 2600 | 470 | 100 | 40.1 | |
A/C 31,350 | - | 2600 | - | 0 | - |
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 |
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. |
Propeller | Altitude | True Airspeed MPH | b.h.p | RPM |
Hub C-532D Blades 89301-3 Std. Spinner | 14,900 | 336.5 | 1000 | 2940 |
Hub C-5315S Blades 618A (Impregnated Wood) Std. Spinner | 15,130 | 332 | 1000 | 2940 |
Hub C-532D Blades 89301-3 wth De-icer Boots Std. Spinner | 15,130 | 333 | 1000 | 2940 |
Hub C-5315S Blades 614ocl.5-12 Std. Spinner | 15,130 | 335.5 | 1000 | 2940 |
3. | Maximum rate of climb at wide open throttle and 2600 RPM. |
15,000 feet | 19,000 feet | 24,000 feet | 28,000 feet | |||||||||
Propeller | R/C F.P.M. | bhp | Vt MPH | R/C F.P.M. | bhp | Vt MPH | R/C F.P.M. | bhp | Vt MPH | R/C F.P.M. | bhp | Vt MPH |
Hub C-532D Blades 89301-3 Std. Spinner | 1500 | 833 | 175.5 | 1140 | 720 | 184 | 685 | 600 | 193 | 340 | 510 | 199 |
Hub C-5315S Blades 618A (Impregnated Wood) Std. Spinner | 1420 | 835 | 175.5 | 1060 | 725 | 182 | 600 | 595 | 190 | 235 | 495 | 198 |
Hub C-532D Blades 89301-3 wth De-icer Boots Std. Spinner | 1460 | 860 | 175.5 | 1100 | 730 | 182 | 660 | 595 | 190 | 300 | 515 | 197 |
Hub C-5315S Blades 614ocl.5-12 Std. Spinner | 1425 | 835 | 175.5 | 1070 | 710 | 182.5 | 615 | 590 | 191.5 | 260 | 505 | 199 |
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 |
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 |
Altitude | True Speed m.p.h. | r.p.m. | b.h.p. | Blower | Throttle | |
9,800 | 320 | 2650 | 1080 | Low | Part | |
12,800 | 350.5 | 3000 | 1240 | Low | Wide (Critical Alt.) | |
16,700 | 336.5 | 2650 | 1010 | High | Part | |
19,270 | 364.5 | 3000 | 1105 | High | *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. |
Altitude | True Speed m.p.h. | r.p.m. | b.h.p. | Rate of Climb Ft./min. | Time of Climb Min. | |
0 | 149 | 2850 | 1135 | 2100 | 0 | |
5,000 | 164 | 2850 | 1180 | 2160 | 2.35 | |
9,600 | 176 | 2850 | 1240 | 2210 | 4.45 | |
13,000 | 185 | 2850 | 1090 | 1780 | 6.2 | |
15,000 | 191 | 2850 | 1085 | 1860 | 7.25 | |
20,000 | 205 | 2850 | 980 | 1480 | 10.2 | |
25,000 | 213.5 | 2850 | 835 | 1000 | 14.25 | |
30,000 | 222 | 2850 | 680 | 530 | 21.0 | |
S/C 34,000 | 229 | 2850 | - | 100 | 37.5 | |
A/C 35,500 | - | 2850 | - | 0 | - |
MEMORANDUM REPORT ON
Pursuit Single Engine P-40F, AAF No. 41-13635
Subject: Propeller Tests |
Section: Flight |
Serial No: FS-M-19-1549-A |
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. |
Propeller | True Airspeed MPH | b.h.p | RPM | |
Hub C-532D Blades 89301-3 Std. Spinner | 355.0 | 1100 | 2950 | |
Hub C-532D Blades 89306-19S Std. Spinner | 356.0 | 1100 | 2950 | |
Hub C-532D Blades 89303-23W Std. Spinner | 353.0 | 1100 | 2950 | |
Hub C-5315 S Blades 61401.5-21 Std. Spinner | 350.5 | 1100 | 2950 | |
(Rotol) Hub RX5/3 Blades RA-675/H Special Spinner | 356.0 | 1100 | 2960 |
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 | |||||||||
Propeller | R/C F.P.M. | bhp | Vt MPH | R/C F.P.M. | bhp | Vt MPH | R/C F.P.M. | bhp | Vt MPH | R/C F.P.M. | bhp | Vt MPH |
Hub C-532D Blades 89301-3 Std. Spinner | 1970 | 1040 | 201.0 | 1540 | 910 | 207.0 | 1220 | 810 | 211.0 | 910 | 715 | 216.0 |
Hub C-532D Blades 89306-19S Std. Spinner | 1460 | 1020 | 201.0 | 1140 | 892 | 207.0 | 910 | 800 | 211.0 | 680 | 702 | 215.0 |
Hub C-532D Blades 89303-24W Std. Spinner | 2010 | 1030 | 200.1 | 1590 | 905 | 207.0 | 1270 | 815 | 211.0 | 960 | 725 | 216.0 |
Hub C-5315 S Blades 6141C1.5-21 Special Spinner | 1630 | 1020 | 201.0 | 1260 | 890 | 207.0 | 990 | 794 | 212.0 | 710 | 700 | 216.0 |
(Rotol) Hub RX5/3 Blades RA-675/H Special Spinner | 1620 | 1005 | 198.5 | 1200 | 865 | 204.5 | 890 | 765 | 209.0 | 580 | 665 | 213.0 |
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 |
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 | RPM | b.h.p. | True Speed MPH | RPM | b.h.p. |
365.5 | 2950 | 1100 | 374 | 2950 | 1100 |
336 | 2650 | 890 | 342 | 2650 | 890 |
311 | 2400 | 760 | 317.5 | 2400 | 760 |
283.5 | 2200 | 635 | 291.5 | 2200 | 635 |
258 | 2000 | 530 | 266 | 2000 | 530 |
233 | 2000 | 445 | 240 | 2000 | 445 |
194 | 2000 | 360 | 200 | 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. |
18,000 | 201 | 2185 | 1040 |
22,000 | 207 | 1725 | 915 |
25,000 | 212 | 1380 | 820 |
28,000 | 217 | 1040 | 710 |
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 |
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 | RPM | b.h.p. | Throttle | Intake Man. Pr. "Hg. | |
2960 | 323 | 3000 | 1125 | Part | - | |
2960 | 344 | 3000 | 1415 | Part | 57 | |
10550 | 348 | 3000 | 1125 | Part | - | |
*10550 | 378 | 3000 | 1480 | Wide | 57 | |
**17300 | 371 | 3000 | 1125 | Wide | - | |
29700 | 348 | 3000 | 706 | Wide | - |
**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 | RPM | b.h.p. | Rate of Climb Ft./Min. | Time of Climb Min. | |
Sea Level | 156.5 | 3000 | 1400 | 3520 | 0 | |
5,000 | 168.5 | 3000 | 1450 | 3640 | 1.39 | |
*8,000 | 174 | 3000 | 1480 | 3720 | 2.21 | |
10,000 | 175.5 | 3000 | 1340 | 3440 | 2.77 | |
15,000 | 180.5 | 3000 | 1105 | 2680 | 4.41 |
*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 | RPM | b.h.p. | Rate of Climb Ft./Min. | Time of Climb Min. | |
Sea Level | 151 | 3000 | 1195 | 3140 | 0 | |
5,000 | 163 | 3000 | 1245 | 3260 | 1.56 | |
10,000 | 175 | 3000 | 1290 | 3375 | 3.07 | |
*10,400 | 176 | 3000 | 1300 | 3380 | 3.19 | |
15,000 | 180.5 | 3000 | 1090 | 2680 | 4.72 | |
20,000 | 186 | 3000 | 905 | 1970 | 6.89 | |
25,000 | 191 | 3000 | 750 | 1400 | 9.89 | |
30,000 | 197 | 3000 | 625 | 890 | 14.33 | |
35,000 | 203 | 3000 | 520 | 400 | 22.52 | |
S/C 38,200 | - | 3000 | - | 100 | 37.37 | |
A/C 39,200 | - | 3000 | - | 0 | - |
*Critical altitude for military power in climb. |
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. |
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 |
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 | RPM | b.h.p. | Throttle | Gross Weight Lb. |
Sea Level | 287 | 1005 | 44.5 | Part | 8300 |
5000 | 306 | 1036 | 44.5 | Part | 8260 |
10000 | 325.5 | 1068 | 44.5 | Part | 8220 |
15000 | 344 | 1100 | 44.5 | Part | 8180 |
*16400 | 350 | 1110 | 44.5 | W.O. | 8170 |
20000 | 342.5 | 977 | 39.2 | W.O. | 8140 |
25000 | 326 | 795 | 32.1 | W.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 | BHP | Manifold Pressure "Hg. | Throttle | Gross Weight Lb. |
Sea Level | 1860 | 0 | 152 | 1020 | 44.5 | Part | 8300 |
5000 | 1900 | 2.66 | 166 | 1055 | 44.5 | Part | 8260 |
10000 | 1935 | 5.27 | 179 | 1085 | 44.5 | Part | 8220 |
*14000 | 1960 | 7.32 | 190 | 1105 | 44.5 | W.O. | 8190 |
20000 | 1310 | 11.02 | 201 | 875 | 35.4 | W.O. | 8140 |
25000 | 760 | 15.93 | 211 | 735 | 29.8 | W.O. | 8090 |
S/C 31000 | 100 | 33.64 | - | - | - | - | - |
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 |
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.
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Speed vs Altitude, XP-40Q-2 42-9987 | |
Climb & Ceiling, XP-40Q-2 42-9987 |
Kittyhawk A.K.572
(Allison V-1710 F.3.R)
Rate of climb and position error measurements.
The performance on climb has been measured at a weight of 8480 lb.
The results show:-
BOSCOMBE DOWN 3 June 1942 Kittyhawk A.L.229
BOSCOMBE DOWN 14 September 1942 Kittyhawk I. A.L.229
BOSCOMBE DOWN 8 October 1942 Kittyhawk I. A.K.751
Handling and performance with a Hydulignum propeller.
BOSCOMBE DOWN 15 October 1942 Kittyhawk II. F.L.220
Climb and level speed performance and position
BOSCOMBE DOWN 6 June 1943 Kittyhawk IA E.T.573
Level speed performance
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Kittyhawk IA E.T.573
(Allison V-1710 F3R)
Level speed performance
with normal cowling fitted.
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 |
Kittyhawk Aircraft P-40E A29-129
(Allison V-1710-F3R)
Part I: Trials with an 83 gallon Belly Fuel Tank. |
An 83 (Imperial) gallon externally carried belly fuel tank of moulded plywood has been treated as an overload item on a Kittyhawk at normal maximum load, and its effect on performance in speed and climb determined. |
On rated power the initial climb is decreased from 2000 ft. per minute to 1580 feet per minute by the addition of the tank. The time to 20,000' is increased from 11.7 minutes to 15.8 minutes, while the estimated service ceiling is decreased from 32,300' to 26,800'. |
The top speed on military power at full throttle height is decreased from 348 m.p.h. at 12,300' to 314 m.p.h. at 12,000'and the top speed on rated power at full throttle height is reduced from 330 m.p.h. at 11,800' to 300 m.p.h. at 11,300' by the addition of the tank. |
The top speed figures have been analysed and making some broad assumptions and with the consumption figures available, a curve is given showing the probable increase in range, at constant indicated airspeed, due to the addition of the tank. |
Part II: An investigation of the effect on top speed of polishing the aircraft. |
The effect of polishing the aircraft in stages has been investigated - |
(a) Polishing control surfaces has no detectable influences on top speed or ontrol characteristics. |
(b) Polishing the mainplanes brought about an increase in the top speed on military power at full throttle height of about 6 m.p.h. |
(c) Polishing the fuselage brought about an increase in top speed on military power of about 1 m.p.h. |
Climbing Trials, Kittyhawk (P-40E) A29-129 |
Speed Trials (without Belly Tank), Kittyhawk (P-40E) A29-129 |
Speed Trials (with Belly Tank), Kittyhawk (P-40E) A29-129 |
BRIEF PERFORMANCE TRIALS OF P-40N AIRCRAFT
(Allison V-1710 - 81)
PART 1. - P-40N - 5CU
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 | |||||
0 | 3000 | 43.8 | 273 | 0 | 2220 |
10000 | 3000 | 43.8 | 310 | 4.4 | 2310 |
15000 | 3000 | 43.8 | 328 | 7.3 | 1960 |
16200 * | 3000 | 43.8 | 332 | - | - |
20000 | 3000 | 37.1xx | 324 | 9.9 | 1460 |
27500 | 3000 | 28.2xx | 294 | - | - |
30000 | 3000 | - | - | 21.6 | 440 |
Normal Rated Power | |||||
0 | 2600 | 39.0 | 266 | 0 | 2060 |
10000 | 2600 | 39.0 | 300 | 4.8 | 2130 |
15000 | 2600 | 39.0 | 318 | 7.7 | 1960 |
15200 * | 2600 | 39.0 | 318 | - | - |
20000 | 2600 | 32.3xx | 309 | 10.3 | 1460 |
27500 | 2600 | 24.5xx | 283 | - | - |
30000 | 2600 | " | - | 22.0 | 440 |
*..... denotes Critical Full Throttle Height
xx..... denotes Level speeds only Service Ceiling - 33500 feet. P40N-5CU A29-418 Climbing Trials - Military Power
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PART 11. - P-40N - 1CU
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 Level | 3000 | 43.8 | 287 | 0.0 | 2300 |
5000 | 3000 | 43.8 | 303 | 2.0 | 2360 |
10000 | 3000 | 43.8 | 321 | 4.1 | 2410 |
x 14000 | 3000 | 43.8 | - | 5.8 | 2450 |
15000 | 3000 | F.T. or 43.8 | 339 | 6.2 | 2335 |
x 17000 | 3000 | F.T. or 43.8 | 346 | 7.1 | - |
20000 | 3000 | F.T. | 340 | 8.5 | 1750 |
25000 | 3000 | F.T. | 328 | 12.2 | 1160 |
30000 | 3000 | F.T. | 307 | 18.2 | 575 |
Normal Rated Power | |||||
Sea Level | 2600 | 39.0 | 274 | 0.0 | 1940 |
5000 | 2600 | 39.0 | 291 | 2.5 | 2000 |
10000 | 2600 | 39.0 | 307 | 5.0 | 2065 |
x 13800 | 2600 | 39.0 | - | 6.8 | 2095 |
15000 | 2600 | F.T. or 39.0 | 324 | 7.4 | 1980 |
x 16100 | 2600 | F.T. or 39.0 | 327 | 8.1 | - |
20000 | 2600 | F.T. | 322 | 10.4 | 1440 |
25000 | 2600 | F.T. | 310 | 14.8 | 895 |
30000 | 2600 | F.T. | 298 | 23.4 | 355 |
x..... denotes Critical Full Throttle Height
Service Ceiling - Undetermined. |
CLIMB PERFORMANCE | ||
WEIGHT 7900 LBS. |
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 Level | 150 | 3000 | 57.0 | 3100 | 0 |
1000 | 150 | 3000 | 57.0 | 3140 | 0.3 |
2000 | 150 | 3000 | 57.0 | 3180 | 0.6 |
3000 | 150 | 3000 | 57.0 | 3220 | 0.95 |
5000 | 150 | 3000 | 57.0 | 3300 | 1.55 |
x 6800 | 150 | 3000 | 57.0 | 3370 | 2.1 |
7500 | 150 | 3000 | 55.5 | 3270 | 2.3 |
10000 | 150 | 3000 | 50.5 | 2930 | 3.1 |
12500 | 147 | 3000 | 46.25 | 2610 | 4.0 |
15000 | 145 | 3000 | 42.25 | 2300 | 5.0 |
x..... denotes Critical Full Throttle Height |
LEVEL SPEEDS | ||
WEIGHT 7900 LBS. |
I.C.A.N. Height Feet | T.A.S. mph | R.P.M. No. | Boost in Hg. |
WAR EMERGENCY RATING | |||
Sea Level | 314 | 3000 | 57.0 |
5000 | 335 | 3000 | 57.0 |
x 9200 | 352 | 3000 | 57.0 |
10000 | 352 | 3000 | 55.25 |
15000 | 348 | 3000 | 46.75 |
x..... denotes Critical Full Throttle Height
P40N-1CU A29-412 Climb Performance W. E. Power Rating
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