56th Fighter Group P-47D
MEMORANDUM REPORT ON
Republic XP-47B, A.C. No. 40-3051
| Subject: Speed Tests |
| Section: Flying Branch |
| Serial No: PHQ-M-19-1288-A |
| A. | Purpose | |
| Flight test of Republic XP-47B Airplane. Equipped with R-2800-35 engine and Curtiss 4 bladed, constant speed propeller, blade design No. 714-1C2-12, with cuffs, set 28° minimum, 58° maximum. Gross weight of airplane was 12,400 lbs. with c.g. at 28.09% m.a.c. Airplane was camaflauged and flown with 6 wing guns installed and second pitot heat located in right outboard gun location. Wheels up; wing flaps neutral; cowl flaps closed; intercooler and oil cooler shutters neutral; radio antenna in place; mixture automatic rich. | ||
| B. | Factual Data | |
| 1. | High speed at 25,800 ft. was 412 m.p.h. at 1960 torque meter b.h.p. at 2700 R.P.M. and 52.6" hg. manifold pressure. | |
| 2. | High speed at 15,600 ft. was 382 m.p.h. at 1970 torque meter b.h.p. at 2700 R.P.M. and 52.6" hg. manifold pressure. | |
| 3. | High speed at 5425 ft. was 344.5 m.p.h. at 1975 torque meter b.h.p. at 2700 R.P.M. and 52.6" hg. manifold pressure. | |
MEMORANDUM REPORT ON
P-47B Airplane, A.C. No. 41-5902
| Subject: Acceptance Performance Tests |
| Section: Flight Section |
| Serial No: PHQ-M-19-1417-A |
| A. | Purpose | |
| 1. | To report results of acceptance performance tests run at the manufacturer's plant on the P-47B airplane, A.C. No. 41-5902 Airplane equipped with Pratt and Whitney R-2800-21 engine with torque meter and exhaust driven turbo supercharger and four-bladed Curtiss electric constant speed propeller with cooling cuffs, blade design No. 714-1C2-12; blade angle range 28° to 58°. Gross weight as tested was 12,565 pounds with the c.g. at 32 percent m.a.c.; wheels up. Radio mast and antenna in place and six .50 caliber machine guns installed. All tests with wheels up, wing flaps up, mixture "auto-rich" and with pointed windshield installed unless otherwise stated. | |
| B. | Test Results | |
| 1. | High speed in level flight with oil cooler flaps and intercooler flaps flush and throttle wide open with turbo on to give military rated power or 18,250 limiting turbo r.p.m. | |
| Altitude Feet | R.P.M. | Manifold Pressure "Hg. | Turbo R.P.M. | Specific Fuel Cons. lbs/hp/hr | B.H.P. | True Speed m.p.h. | |
| 5,000 | 2700 | 52.0 | 6,800 | .78 | 2000 | 352 | |
| 15,000 | 2700 | 51.0 | 11,800 | .77 | 2000 | 386 | |
| 25,000 | 2700 | 51.7 | 16,900 | .78 | 2000 | 420 | |
| 27,800 | 2700 | 52.0 | 18,250 | - | 2000 | 429 | |
| 30,000 | 2700 | 47.5 | 18,250 | - | 1845 | 426 | |
| 34,000 | 2700 | 40.0 | 18,250 | - | 1575 | 412 | |
| 6. | Climb data obtained with throttle wide open, and turbo on to give rated power or 18,250 turbo r.p.m. Cowl flaps, oil cooler flaps and intercooler flaps wide open. |
| Altitude Feet | True Speed m.p.h. | R.P.M. | Manifold Pressure "Hg. | Turbo R.P.M. | b.h.p. | Rate of Climb Ft/Min | Time of Climb Min. | Remarks | |
| 0 | 172 | 2700 | 52.7 | 5,600 | 2000 | 2560 | 0 | Military Power | |
| 5,000 | 183 | 2700 | 51.6 | 8,200 | 2000 | 2545 | 1.95 | Climb for 5 Min. | |
| 10,000 | 196 | 2700 | 50.6 | 10,600 | 2000 | 2465 | 3.95 | ||
| 12,600 | 204 | 2700 | 50.4 | 11,750 | 2000 | 2410 | 5.00 | ||
| 12,600 | 195 | 2550 | 39.6 | 9,400 | 1625 | 1800 | - | Rated Power | |
| 15,000 | 200 | 2550 | 39.4 | 10,650 | 1625 | 1725 | 6.7 | (Climb after | |
| 20,000 | 217 | 2550 | 39.2 | 13,200 | 1625 | 1565 | 9.75 | (5 Min. Military | |
| 25,000 | 236 | 2550 | 39.6 | 15,700 | 1625 | 1380 | 13.2 | (Power climb | |
| 30,000 | 270 | 2550 | 40.1 | 18,250 | 1625 | 1140 | 17.1 | Crtitical Alt. | |
| 35,000 | 305 | 2550 | 35.9 | 18,250 | 1365 | 450 | 23.9 | ||
| See also: | Memorandum Report PHQ-M-1417-A, Addendum 1 |
MEMORANDUM REPORT ON
P-47B Airplane, AC No. 41-5931
| Subject: Performance Tests |
| Section: Flight |
| Serial No: FS-M-19-1469-A |
| A. | Purpose | |
| 1. | To report results of flight tests conducted to determine the rate
of climb and the level flight critical altitude at military power on the P-47B airplane AC No. 41-5931. This airplane equipped
with Pratt & Whitney R-2800-21 engine with turbo supercharger and four-bladed Curtiss electric constant speed propeller with cooling
cuffs; blade design No. 714-1C2-12; blade angle range 28° to 58°. Gross weight as tested was 12,560 pounds at 32 percent m.a.c.,
wheels up. Radio mast and antenna in place and eight .50 caliber machine guns installed. All tests with wheels up, wing flaps up, and with the mixture automatic rich.
No torque meter was installed on this airplane so that power data was not obtained. However, from torque meter data on other P-47B airplane tests, military rated power of 2000 b.h.p. at 2700 RPM would be obtained at aprroximately 52.2" Hg. at 25,000 feet on this airplane | |
| B. | Test Results | |
| 1. | Critical altitude in level flight for approximately 2000 b.h.p. at 2700 RPM at 18,250 turbo RPM with cowl flaps, oil cooler, and intercooler flaps flush and throttle wide open with turbo on to give 18,250 turbo RPM. | |
| Condition | Critical Altitude | True Speed | Manifold Pressure | |
| Original duct without dust screen | 26,800 | 429 | 52.3 | |
| New duct with dust screen inst. | 24,900 | 419 | 52.4 | |
| New duct with dust screen by-passed | 25,200 | 421 | 52.6 | |
| New duct with dust screen removed | 25,600 | 423 | 52.8 | |
| 2. | Climb data obtained with throttle wide open, and turbo on to give 52.2" Hg. or 18,250 turbo RPM. Cowl flaps, oil cooler flaps and intercooler flaps wide open. Original intake duct without dust screens installed. |
| Altitude Ft. | True Speed MPH | RPM | Manifold Pressure "Hg. | Turbo RPM | Rate of Climb ft/min | |
| 15,000 | 207 | 2700 | 51.8 | 14,050 | 2330 | |
| 20,000 | 233 | 2700 | 52.0 | 16,450 | 2150 | |
| 23,400 | 245 | 2700 | 52.2 | 18,250 | 2000 | |
| 25,000 | 252 | 2700 | 49.2 | 18,250 | 1810 | |
| 30,000 | 265 | 2700 | 41.0 | 18250 | 1190 | |
| 35,000 | 272 | 2700 | 32.7 | 18250 | 570 | |
MEMORANDUM REPORT ON
P-47B Airplane, A.C. No. 41-5942
| Subject: Comparitive Propeller Tests |
| Section: Flight Section |
| Serial No: FS-M-19-1523-A |
| A. | Purpose | |
| 1. | To report results of flight tests of six four-bladed propellers installed on P-47B airplane. Tests were run at Republic Factory, Farmingdale, New York. Airplane equipped with Pratt and Whitney, R-2800-21 engine with torque meter and with an exhaust driven turbo supercharger. Gross weight as tested was 12,620 pounds at 30.32 percent m.a.c. wheels up. Radio mast and antenna in place, and eight .50 caliber machine guns installed. All tests with wheels and up and with mixture auto-rich. | |
| 2. | Propellers, design Nos. 814-103-24A, 714-1C2-12, and 814-3C3-18 were fitted with cooling cuffs. | |
| B. | Test Results | |
| 1. | High speed at 2000 torque meter b.h.p. at 2700 RPM at 5000 feet, 25,000, and at critical altitude for 2000 b.h.p. at 18,250 turbo RPM. Cowl flaps closed, intercooler and oil cooler shutters neutral. | |
| True Speed - MPH | |||||||
| Curtiss | Ham. Std. | ||||||
| Altitude | 12'2" | 13'2" | 13'6" | 12'2" | 12'2" | 13'0" | |
| Feet | 714-1C2-12 | 814-1C3-24A | 814-3C3-18 | 101348-12 | 101350-12 | 6501A-0 | |
| 5,000 | 353 | 343 | 337 | 352 | 350 | 347 | |
| 25,000 | 419 | 402 | 397 | 418 | 415 | 414 | |
| Critical Altitude | 428 at 28,000 ft. | 408 at 27,000 ft. | 406 at 28,000 ft. | 426 at 27,400 ft. | 425 at 28,200 ft. | 424 at 28,200 ft. | |
| 2. | Climb data obtained with throttle wide open and turbo on to give either 2000 torque b.h.p. or 18,250 turbo RPM at 2700 engine RPM. Cowl flaps, oil cooler flaps, and intercooler flaps wide open. |
| Rate of Climb - Ft./Min. | ||||||
| Propeller | 10,000 | 15,000 | 20,000 | *24,000 | 30,000 | |
| Curtiss 12'2" 714-1C2-12 | 2420 | 2350 | 2180 | 1960 | 1180 | |
| Curtiss 13'2" 814-1C3-24A | 2600 | 2540 | 2400 | 2200 | 1320 | |
| Curtiss 13'6" 814-3C3-18 | 2610 | 2560 | 2400 | 2200 | 1410 | |
| Curtiss 12'2" 101348-12 | 2590 | 2530 | 2390 | 2180 | 1320 | |
| Curtiss 12'2" 101350-12 | 2600 | 2550 | 2405 | 2210 | 1300 | |
| Ham. Std. 13' 6501A-0 | 2700 | 2620 | 2460 | 2270 | 1400 | |
| Torque b.h.p. | 2000 | 2000 | 2000 | 2000 | 1645 | |
| True Speed | 185 | 201 | 218 | 233 | 250 | |
| *Critical altitude for 2000 b.h.p. at 18,250 turbo RPM. |
MEMORANDUM REPORT ON
P-47B Airplane, A.C. No. 41-5942
| Subject: Comparitive Propeller Tests |
| Section: Flight |
| Serial No: FS-M-19-1533-A |
| A. | Purpose | |
| 1. | To report results of flight tests of the P-47B airplane, AC No. 41-5942, conducted at the manufacturer's plant in order to obtain comparative performance with a 13 feet 0 inch diameter, No. 826, Curtiss test propeller and with the standard production propeller No. 714-1C2-12: cuffs were not installed on either propeller. Airplane equipped with Pratt and Whitney R-2800-21 engine with torque meter and with an exhaust driven turbo super-charger. Gross weight at take-off for all tests was 12,620 pounds at 28.3 percent m.a.c., wheels up. Radio mast and antenna in place and eight .50 caliber machine guns installed. All tests with wheels and flaps up and with the mixture auto-rich. | |
| B. | Test Results | |
| 1. | High speed at 2700 RPM and 2000 b.h.p. at 5000 feet, 25,000, and critical altitude for 18,250 turbo RPM. Cowl flaps closed, intercooler and oil cooler flaps neutral. | |
| True Speed - MPH | |||
| Altitude Feet | Curtiss Prop. No. 826 13 ft. 0 in. Dia. | Curtiss Prop. No. 714-102-12 12 ft. 2 in. Dia. | |
| 5,000 | 342 | 350 | |
| 25,000 | 408 | 414 | |
| Critical Altitude | 415 at 27,000 ft. | 421 at 27,300 ft. | |
| 2. | Climb data obtained with throttle wide open and turbo on to give either 2000 torque b.h.p. or 18,250 turbo RPM. Cowl flaps, oil cooler flaps, and intercooler flaps wide open. |
| Rate of Climb - ft/min. | |||||
| Altitude Feet | I.A.S. MPH | Torque b.h.p. | Curtiss No. 826 13 ft. 0 in. Dia. | Curtiss No. 714-102-12 12 ft. 2 in. Dia. | |
| 10,000 | 185 | 2000 | 2720 | 2580 | |
| 15,000 | 201 | 2000 | 2610 | 2440 | |
| 20,000 | 218 | 2000 | 2440 | 2240 | |
| 23,300* | 231 | 2000 | 2295 | 2080 | |
| 25,000 | 236 | 1900 | 2040 | 1850 | |
| 30,000 | 252 | 1620 | 1345 | 1190 | |
| 35,000 | 255 | 1350 | 700 | 550 | |
| *Critical altitude for 2000 b.h.p. at 18,250 turbo RPM. | |
| Note: Above speeds are the same speeds as used for climbs in previous propeller tests on this airplane and are the minimum speeds at which the climbs can be made without overheating on a normal day. |
TACTICAL SUITABILITY OF THE P-47C-1 TYPE AIRCRAFT
18 December 1942
| a. The P-47C-1 is the best high altitude fighter aircraft now in production with regard to high speed, stability, pilot comfort, height and armament.
b. The rate of climb is not as good as desired, which fact limits its suitability as a medium altitude fighter and as an interceptor. c. All weight in the structure and accessories not vital to operational use should be eliminated. d. The aircraft is pleasant and easy to fly. New pilots should have no trouble being checked out in it. e. The rate of aileron roll is the best found in any type of American fighter. f. The view over the nose is not great enough to allow desired deflection shooting. g. The demand type oxygen installation is satisfactory, but the service type mask with this installation is bulky, heavy, cumbersome and irritating to the pilot. h. It is dangerous to attempt to take-off with mixture control in full rich position. i. In a glide with engine idling, engine tends to load up and difficulty is encountered starting up engine again. j. The hook-up of the throttle, R.P.M., and turbo control handles to operate as one if desired is very satisfactory. k. With the present ceiling now obtainable with this aircraft, and the added height with new modifications, experiments should be pushed to perfect a pressurized cockpit on this type plane now. |
MEMORANDUM REPORT ON
P-47D Airplane, AAF No. 42-74616
| Subject: Comparitive Propeller Tests |
| Section: Flight |
| Serial No: Eng-47-1649-A |
| A. | Purpose | |
| 1. | To report results of performance tests conducted at Wright Field on the P-47D Airplane No. 42-74616. | |
| B. | Factual Data and Test Results | |
| 1. | Airplane equipped with Pratt and Whitney R-2800-21 turbo supercharged engine with A-17 turbo regulator and a hollow steel four blade A. O. Smith propeller with extended trailing edges, blade design No. X43M17611. All power figures at 2700 rpm based on a power curve drawn from torque meter data obtained on a P-47B with the same engine. Cruise power figures based on a power curve No. T-771, dated 14 July 1941. | |
| 2. | Configuration was normal with all flights at a gross weight at take-off of 13,200 pounds with c.g. at 27.44% m.a.c., gear up. Total useful load included 300 gallons of fuel, 28 gallons of oil, 525 pounds of ballast in the ammunition boxes, and the pilot. All radio equipment installed; four, 50 cal. M.G. in each wing, wing flaps neutral, carburetor cold, and gear up. | |
| 3. | High speeds in level flight at 2700 rpm with mixture auto-rich, cowl flaps closed, and oil and intercooler flaps neutral. | |
| Altitude Ft. | True Speed MPH | Intake Manifold Pressure "Hg. | Exhaust Back Pressure "Hg. | Brake Horsepower | Turbo RPM | |
| 5,500 | 329.5 | 53.5 | 32.4 | 2000 | 14,400 | |
| *27,000 | 417.0 | 52.2 | 30.4 | 2000 | 18,250 | |
| 27,800 | 415.0 | 50.6 | 29.5 | 1950 | 18,250 | |
| 4. | Climb performance at 2700 rpm with mixture auto-rich and cowl, oil, and intercooler flaps wide open. |
| Altitude Ft. | Rate of Climb Ft./Min. | Intake Manifold Pressure "Hg. | Brake Horsepower | True Speed MPH | |
| 0 | 2305 | 52.4 | 2000 | 164.0 | |
| 5,000 | 2215 | 52.6 | 2000 | 176.5 | |
| 10,000 | 2120 | 52.2 | 2000 | 191.0 | |
| 15,000 | 2020 | 52.0 | 2000 | 206.5 | |
| 20,000 | 1900 | 52.1 | 2000 | 224.5 | |
| *23,800 | 1805 | 52.6 | 2000 | 240.0 | |
| 25,000 | 1635 | 50.2 | 1915 | 243.5 | |
| 30,000 | 1040 | 41.9 | 1620 | 256.5 | |
| 35,000 | 505 | 34.0 | 1370 | - | |
| S/C 39,000 | 100 | 28.0 | 1205 | - | |
| A/C 40,000 | 0 | 26.6 | 1170 | - | |
| *Critical Altitude in climb for 18,250 limiting turbo speed. |
MEMORANDUM REPORT ON
P-47D-10 Airplane, AAF No. 43-75035
| Subject: Results of Flight Tests |
| Section: Flight |
| Serial No: Eng-47-1652-A |
| A. | Purpose | |
| 1. | To report results of flight tests on P-47D-10 airplane, AAF No. 43-75035 run at the manufacturer's plant. Airplane equipped with Pratt & Whitney R-2800-63 engine with water injection; standard Curtiss 714-1C2-12 propeller; type A-17 turbo regulator. Airplane ballasted to simulate the following conditions: Six .50 caliber guns; 300 rounds per gun; 305 gallons gasoline; 15 gallons water; 14 pounds pyrotechnics. In this condition the gross weight was 13,234 pounds with a C.G. wheels up, of 29.63 percent M.A.C. Mixture auto-rich; throttle wide open on all tests. Horsepower data obtained with torquemeter. | |
| B. | Results | |
| 1. | High speed: Intercooler and oil cooler flap neutral, cowl flaps closed; flaps and gear up; 2700 R.P.M. with water injection. | |
| Altitude Ft. | Manifold Pressure "Hg. | Torque Brake Horsepower | Turbo RPM | Exhaust Back Press. "Hg. | Carb. Air Temp. °C | True Speed MPH | |
| 0 | 56 | 2210 | 7,200 | 36.0 | 32.0 | 333 | |
| 5,000 | 56 | 2265 | 9,400 | 33.2 | 27.0 | 353 | |
| 10,000 | 56 | 2315 | 11,600 | 31.4 | 23.0 | 372 | |
| 15,000 | 56 | 2335 | 13,850 | 30.3 | 23.0 | 390 | |
| 20,000 | 56 | 2325 | 16,200 | 30.5 | 26.0 | 406 | |
| 25,000 | 56 | 2265 | 18,650 | 32.5 | 33.0 | 421 | |
| 30,000 | 56 | 2225 | 21,400 | 35.7 | 43.0 | 433 | |
| 31,000 | 56 | 2220 | 22,000 | 36.5 | 46.0 | 435 | |
| 33,000 | 50.5 | 2020 | 22,000 | 32.0 | 39.0 | 430 | |
| 35,000 | 45.8 | 1740 | 22,000 | 30.0 | 32.0 | 422 | |
| 38,000 | 39.0 | 1550 | 22,000 | 25.3 | 23.0 | 404 | |
| 2. | Climbs: Cowl flaps wide open; intercooler and oil cooler flaps wide open; flaps and gear up; 2700 RPM with water injection. |
| Altitude Ft. | Manifold Pressure "Hg. | Torque Brake Horsepower | Turbo RPM | Carb. Air Temp. °C | Exhaust Back Press. "Hg. | Rate of Climb Ft/Min. | |
| 0 | 56 | 2200 | 7,300 | 26.0 | 37.0 | 2870 | |
| 5,000 | 56 | 2285 | 10,400 | 24.5 | 35.5 | 2810 | |
| 10,000 | 56 | 2320 | 12,850 | 23.5 | 34.5 | 2680 | |
| 15,000 | 56 | 2330 | 15,100 | 24.0 | 34.0 | 2460 | |
| 20,000 | 56 | 2320 | 17,200 | 27.5 | 34.5 | 2180 | |
| * 25,000 | 56 | 2280 | 20,000 | 34.5 | 36.5 | 1860 | |
| ** 28,000 | 53.5 | 2150 | 22,000 | 40.0 | 36.5 | 1520 | |
| 30,000 | 51 | 2070 | 22,000 | 37.5 | 35.0 | 1400 | |
| 34,000 | 43.5 | 1780 | 22,000 | 28.5 | 30.0 | 950 | |
| 38,000 | 37.5 | 1520 | 22,000 | 20.0 | 25.0 | 500 | |
| * Critical altitude for 56 inches manifold pressure due to A-17 type turbo-regulator. |
| See also: | Memorandum Report Eng-47-1652-A, Addendum 1 |
MEMORANDUM REPORT ON
P-47D-10 Airplane, AAF No. 43-75035
| Subject: Comparative Propeller Tests |
| Section: Flight |
| Serial No: Eng-47-1714-A |
| Climb performance of Curtiss 836-2C2-18 propeller and Hamilton Standard 6507A-2 propeller was nearly identical, the difference between the two being within the limits of experimental accuracy.
A definite difference of performance in level flight high speeds was found, with the Hamilton Standard propeller giving from five to eight miles per hour faster speeds throughout the altitude tested.
Results of tests on Curtis 836-2C2-18 with standard cuffs and tip vent holes showed no increase in speed at 24,000 ft., and a slightly higher rate of climb than that obtained on the 836-2C2-18 without vents. This increase in rate of climb was within the limits of experimental accuracy. Also, since no increase in speed was obtained by adding the vent holes on the blade tips, no increase in rate of climb would be expected. Level flight high speed tests run on the Curtiss 836-2C2-18 propeller with tip vent holes, pentrate finish and experimental "C" type Curtiss cuffs showed a small trend toward improvement over the Curtiss 836-2C2-18 with standard cuffs, and tip vent holes at horsepowers above 2000. This is shown in Fig. 5. Level flight high speed tests run on the Curtiss 836-2C2-18 propeller with a flattened blade shank, tip vent holes, pentrate, and experimental "D" type cuffs also showed a small trend toward improvement over the 836-2C2-18 wth standard cuffs, and tip vent holes at horsepowers above 2000 as shown in Fig. 5. A comparison of climb and level flight performance is given in Fig. 2. |
FLIGHT TESTS ON THE REPUBLIC
P-47D AIRPLANE, AAF NO. 42-26167
USING 44-1 FUEL
| Preliminary tests were run to clear the airplane for performance with higher powers with and without water injection.
Detonation equipment was installed to determine if any flight condition became marginal as to detonation, cooling or improper operation of auxiliary parts.
No detonation was observed in level flight up to 65.0" Hg. without water and 70.0" with water.
No detonation was observed in climb up to 65" Hg. without water.
Detonation occurred at 65.0" with water in climb but was remedied by using a No. 18 water jet.
Cylinder head and carburetor air temperatures remained below the limits in level flight.
Excessive cylinder head and carburetor air temperatures were encountered in climbs, limiting the duration of any climb to a point where limits are reached.
The airplane and engine handled well at all altitudes at the higher powers. At 70.0" Hg., water injection, a maximum speed of 444 MPH was obtained at 23,200 feet. At 65.0" Hg., with water a high speed of 439 MPH at 25,200 feet and a maximum rate of climb of 3260 ft/min. at 10,000 feet were obtained. At 65.0" Hg., without water a high speed of 430 MPH at 25,400 feet and a maximum rate of climb of 2850 ft/min. at 12,000 feet were obtained. At 56.0" Hg. without water a high speed of 418 MPH at 29,600 feet and a maximum rate of climb of 2330 ft/min. at 12,000 feet were obtained. At 52.0" Hg. without water a high speed of 412 MPH at 31,400 feet and a maximum rate of climb of 2030 ft/min. at 12,000 feet were obtained. |
Comparison of P-47D, P-47M and P-47N Performance
| P-47D | P-47M | P-47N | |
| High Speed at S.L. | 345 | 367 | 359 |
| " " " 10,000 | 383 | 401 | 392 |
| " " " 20,000 | 417 | 436 | 423 |
| " " " 32,000 | 435 | 473 | 457 |
| R/C at S.L. | 3180 | 3960 | 3580 |
| " " 10,000 | 2920 | 3740 | 3500 |
| " " 20,000 | 2470 | 3300 | 3150 |
| " " 32,000 | 1100 | 2180 | 1840 |
| Combat Radius | 600 | 400 | 1310 |
| Combat Weight | 12,731 | 13,262 | 15,790 |
| War Emergency Power | 2,600 | 2,800 | 2,800 |
| The high speed of the P-47D at 32,000 is estimated, otherwise all performance figures are actual. All power is at war emergency, airplane in combat condition. |
| Comparison of P-47D, P-47M and P-47N Performance |
| List of Essential Differences Between the P-47D, P-47M and P-47N |
| P-47M and P-47N High Speed Performance at Altitude |
| P-47M and P-47N Rate of Climb Performance at Altitude |
| REPUBLIC AVIATION | ||
| Corporation | Report No. ES-300 | |
| Farmingdale, L. I., New York | Model AP-16a |
Model Specification for
Republic Model AP-16a
Fighter Offensive
Air Corps Type Designation P-47M
| Performance (With Design Useful Load) | |||
| (1). Guaranteed Performance | |||
| (a) | High Speed at 38,750 ft. (Critical Altitude) with 2100 BHP | 462 MPH | |
| (b) | High Speed at 15,000 ft. with 2100 BHP | 383 MPH | |
| (c) | High Speed at 5,000 ft. with 2100 BHP | 350 MPH | |
| (d) | High Speed at 42,000 ft. (Critical Altitude) with 1700 BHP | 441 MPH | |
| (e) | Operating Speed at 32,000 ft. (Design Alt.) with 1270 BHP (75% Normal Rated Power & 91% Rated RPM) | 360 MPH | |
| (f) | Endurance at Operating Speed with normal fuel load (205 gals.) | 1.48 hrs. | |
| (g) | Time to Climb to 15,000 ft. | 5.7 min. | |
| (h) | Take-Off over a 50 ft. obstacle within | 2,200 ft. | |
| (i) | Landing over a 50 ft. obstacle, within | 2,150 ft. | |
| (j) | Landing Speed with Flaps retracted | 118 MPH | |
| (k) | Landing Speed with Flaps extended | 99 MPH | |
| (l) | Cruising Speed at 20,000 ft., 820 BHP at 1800 RPM | 246 MPH | |
| (m) | Range at Cruising Speed with 205 gals. of fuel | 785 miles | |
| (2). Additional Performance | |||
| (a) | High Speed at 32,000 ft. (Critical Altitude) with 2800 BHP (W.E.P.) | 473 MPH | |
| (b) | High Speed at 15,000 ft. with 2800 BHP | 418 MPH | |
| (c) | High Speed at 5,000 ft. with 2800 BHP | 384 MPH | |
| (d) | Time to Climb to 15,000 ft. with 2800 BHP | 4.2 min. | |
| (e) | Take-Off over a 50 ft. obstacle, at 2800 BHP within | 1,800 ft. | |
| REPUBLIC AVIATION | ||
| Corporation | Report No. ES-302-A | |
| Farmingdale, L. I., New York | Model AP-16b |
Model Specification for
Republic Model AP-16b
Fighter Offensive
Fighter Bomber
VLR Escort Fighter
Air Corps Type Designation P-47N-5-RE
| Performance Condition I Fighter Offensive | |||
| The performance here listed shall be for normal gross weight with normal load of 13962#. | |||
| (1). Guaranteed Performance | |||
| (a) | High Speed at 38,750 ft. (Critical Altitude) with 2100 BHP | 453 MPH | |
| (b) | High Speed at 15,000 ft. with 2100 BHP | 379 MPH | |
| (c) | High Speed at 5,000 ft. with 2100 BHP | 345 MPH | |
| (d) | High Speed at 42,000 ft. (Critical Altitude) with 1700 BHP | 438 MPH | |
| (e) | Operating Speed at 32,000 ft. (Design Alt.) with 1270 BHP (75% Normal Rated Power & 91% Rated RPM) | 350 MPH | |
| (f) | Endurance at Operating Speed with normal fuel load (205 gals.) | 1.48 hrs. | |
| (g) | Time to Climb to 15,000 ft. | 6.2 min. | |
| (h) | Take-Off over a 50 ft. obstacle within | 2,350 ft. | |
| (i) | Landing over a 50 ft. obstacle, within | 2,150 ft. | |
| (j) | Landing Speed with Flaps retracted | 117 MPH | |
| (k) | Landing Speed with Flaps extended | 98 MPH | |
| (l) | Cruising Speed at 25,000 ft., 800 BHP at 1900 RPM | 274 MPH | |
| (m) | Range at Cruising Speed with 205 gals. fuel | 740 miles | |
| Note: - Performance at high speed is decreased 11 MPH when rocket supports are attached and 21 MPH additional when rockers are carried on supports. | |||
| (2). Additional Performance | |||
| (a) | High Speed at 32,000 ft. (Critical Altitude) with 2800 BHP (W.E.P.) | 467 MPH | |
| (b) | High Speed at 15,000 ft. with 2800 BHP | 417 MPH | |
| (c) | High Speed at 5,000 ft. with 2800 BHP | 384 MPH | |
| (d) | Time to Climb to 15,000 ft. with 2800 BHP | 4.6 min. | |
| (e) | Take-Off over a 50 ft. obstacle, at 2800 BHP within | 1,950 ft. | |
FLIGHT TESTS OF THE P-47N AIRPLANE
AAF NO. 44-88406
Summary
| The P-47 N airplane has performance and handling characteristics very similar to the early P-47 airplanes, but due to heavier weights caused by greater fuel capacity, performance is lower when using equal power settings. The rate of roll is slower, due to the weight being farther from the longitudinal axis of the airplane.
Control forces are good, but as in the earlier model P-47 airplanes large changes in trim are necessary for a change in airspeed. The principal performance in the various configurations is summarized in the following table. Military power is the power available at 2800 rpm and 53.0 Hg and normal rated power is the power available at 2600 rpm and 42.5 Hg. Cowl flaps are closed in level flight and full open in climbs. |
| Configuration | |||
| Clean-Wing Racks only at 16,400 lbs at Take-off | 2 - 165 Gal. Wing Tanks 19,250 lbs at Take-off | 2 - 165 Gal. Wing Tanks, 1-110 Gal. Belly Tank- 19,880 lbs. at Take-off | |
| Maximum Speed at Military Power (mph) | 423 | (38,000) | |
| High Speed at S.L. at Military Power (mph) | 327 | ||
| High Speed at 15,000 ft. at War Emergency Power (mph) | 405 | ||
| High Speed at 15,000 ft. at Military Power (mph) | 372 | ||
| High Speed at 15,000 ft. at Normal Rated Power (mph) Auto-Rich | 346 | 320 | 307 |
| Maximum Air Miles per Gallon at 15,000 ft., 185 mph IAS (240 True Air Speed) | 3.6 | 2.85 | 2.55 |
| R/C S.L. at Military Power (Ft/Min) | 1600 | ||
| S/C at Military Power (ft) | 40,400 | ||
| T/C to 20,000 ft. at Military Power (min) | 11.6 | ||
| R/C at 20,000 ft. at Normal Rated Power (Ft/Min) | 1320 | 680 | 540 |
| T/C to 20,000 ft. at Normal Rated Power (min) | 14.0 | 24.5 | 29.1 |
| With the exceptions of climbs with external drag items installed, the test airplane compares reasonably well with the technical order.
At high power settings considerable maintenance was involved because of oil leaks, cracked vacuum pump housings, exhaust collector rings burning out and oil leaks. At war emergency power these malfunctions become excessive and operation was restricted at this power. In military power climbs high oil and cylinder head temperature above 30,000 ft. were experienced and made it necessary to reduce power after ten minutes of operation to cool the engine. |
