P-47 Performance Tests

P-47 Performance Trials

56th Fighter Group P-47D

WAR DEPARTMENT
AIR CORP, MATERIAL DIVISION
Wright Field, Dayton, Ohio
June 18, 1942
P-47B Airplane, A.C. No. 41-5902
Acceptance Performance Tests

Summary
        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

        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

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ARMY AIR FORCES
MATERIAL CENTER
Wright Field, Dayton, Ohio
December 26, 1942
P-47B Airplane, A.C. No. 41-5942
Comparitive Propeller Tests

Summary
        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.

        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.
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ARMY AIR FORCES
MATERIAL CENTER
January 28, 1943
P-47B, A.C. No. 41-5942
Comparitive Propeller Tests

Summary
        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.

        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.
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ARMY AIR FORCES
PROVING GROUND COMMAND
Eglin Field, Florida
TACTICAL SUITABILITY OF THE P-47C-1 TYPE AIRCRAFT
18 December 1942

Conclusions

   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.

For more of this report see HERE

ARMY AIR FORCES
MATERIAL COMMAND
Wright Field, Dayton, Ohio
28 September 1943
P-47D Airplane, AAF No. 42-74616
Comparitive Propeller Tests

Summary
        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

       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.
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ARMY AIR FORCES
MATERIAL COMMAND
Wright Field, Dayton, Ohio
11 October 1943
P-47D-10 Airplane, AAF No. 43-75035
Results of Flight Tests

Results
       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

       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.
Speed vs Altitude
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ARMY AIR FORCES
MATERIAL COMMAND
Wright Field, Dayton, Ohio
27 March 1944
P-47D-10 Airplane, AAF No. 43-75035
Comparative Propeller Tests

Conclusions
        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.
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ENGINEERING DIVISION MEMORANDUM
REPORT SERIAL NO. ENG-47-1774-A
15 July 1944
FLIGHT TESTS ON THE REPUBLIC
P-47D AIRPLANE, AAF NO. 42-26167
USING 44-1 FUEL

Summary
       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.
       Speed in Level Flight
       Rate of Climb & Ceiling
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ARMY AIR FORCES
MATERIAL CENTER
Wright Field, Dayton, Ohio
6 October 1944
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

October 14, 1944
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.

Performance at Altitude, Model P-47M

REPUBLIC AVIATION
Corporation Report No. ES-302-A
Farmingdale, L. I., New York Model AP-16b

15 April 1945
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.

Performance at Altitude, Model P-47N-5 RE

FLIGHT TEST DIVISION MEMORANDUM
REPORT SERIAL NO. TSFTE-2012
17 September 1946
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.
For more of this report see HERE

Notes
Preliminary Report of 7-1/2 Hour War Emergency Test of Pratt & Whitney R-2800-63 Engine using Power Plant Fuel 44-1
P-47D released for 70 In. Hg MAP using 100/150 fuel with water injection, 24 June 1944
Fighter Comparison Chart
P-47 Tactical Planning Characteristics & Performance Chart

Main Encounter Reports of P-47 Pilots AFDU Tactical Trials - P-47C VIII Fighter Command: Tests on P-47C's

Work in Progress

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

	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.

	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

	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.

			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

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

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	-

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

	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

	REPUBLIC AVIATION
	Corporation	Report No. ES-300
	Farmingdale, L. I., New York	Model AP-16a

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

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.


	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