Performance Tests on the Lockheed
P-80 A-1 Airplane, AAF No. 44-85044
The P80A-1 airplane, AAF No. 44-85044, is a standard production model, equipped with a J-33 engine.
The tail pipe was 18 1/2" in diameter. The external drag configuration of the aircraft is shown in photographs in Appendix C.
It was necessary to change engines during the tests. The engine used is listed with the performance obtained throughout this report. The engines were as follows: |
Engine No. 1 - J-33-GE-11 | Serial No. 006137 |
Engine No. 2 - J-33-GE-11 | Serial No. 006112 |
Engine No. 3 - J-33-A-9 | Serial No. 071401 |
The principle performance results at 11,500 R.P.M. at weights corresponding to Section VI, Paragraphs B & C are as follows:
A. Level flight high speed comparison at 11,500 R.P.M. |
True Speed - M.P.H. | |||
Pressure Altitude Ft. | Clean Configuration Engine No. 1 | Clean Configuration Engine No. 2 | Two 165 Gal. Tip Tanks Engine No. 2 |
Sea Level | 510 | ----- | 494 |
10,000 | 518 | ----- | 512 |
20,000 | 520 | ----- | 513 |
25,000 | 519 | 534 | 507 |
30,000 | 515 | 526 | 497 |
35,000 | 507 | 512 | 485 |
40,000 | 495 | ----- | 472 |
Additional Checks were obtained of the high speed in the clean configuration when equipped with No. 3 engine at approximately 5,000 ft. and 30,000 ft.
The results showed the airplane to be approximately 15 M.P.H. faster than with No. 1 engine.
B. Rate of climb and time to climb comparison at 11,500 R.P.M. and at weights cooresponding to Section VI, Paragraph C, are as follows: All data with Engine No. 2 at the speeds for maximum rate of climb recommended by the Lockheed Aircraft Corp. |
Rate of Climb - Ft./min. | Time to Climb - min. | |||
Pressure Altitude Ft. | Clean | Tip Tanks | Clean | Tip Tanks |
Sea Level | 4640 | 3300 | 0 | 0 |
10,000 | 3730 | 2510 | 2.4 | 3.4 |
20,000 | 2830 | 1720 | 5.5 | 8.2 |
30,000 | 1910 | 925 | 9.8 | 16.4 |
40,000 | 400 | ---- | 19.0 | ---- |
Memorandum Report on
The P-80A-5LO Airplane, AAF No. 44-85462
7 November 1946
The effect of filler and paint on the level flight performance of this P-80A airplane has been summarized in the following table: |
Altitude Ft. | Surface Finish | ||||
Unpainted 10,200 lbs. | Filled 10,215 lbs. | Painted 10,260 lbs. | |||
Maximum True Airspeed | 5,000 | 526 | 533 | 536 | |
at 11,500 | 20,000 | 521 | 528 | 530 | |
34,000 | 504 | 505 | 505 | ||
Cruising True Airspeed | 5,000 | 421 | 426 | 429 | |
at 10,400 | 20,000 | 434 | 442 | 445 | |
34,000 | 431 | 439 | 444 | ||
Memorandum Report on
The P-80A-1, AAF No. 44-85123
3 December 1946
The effect of the modified nose and clipped wing tips on the level flight performance of this aircraft have been summarized in the following table: |
Altitude Ft. | Mod. Nose & Clipped Wing Tips Gr. Wt. 11,480 Lbs. | Mod. Nose & Std. Wing Tips Gr. Wt. 11,560 Lbs. | Std. Nose & Std. Wing Tips Gr. Wt. 11,750 Lbs. | |
Maximum | 2700 | 562 | 556 | 548 |
True Airspeed | 7600 | 561 | 554 | 546 |
At | 12000 | 557 | 550 | 542 |
11,500 RPM | 34700 | 505 | --- | 501 |
Cruising | 2700 | 445 | 439 | 435 |
True Airspeed | 7600 | 452 | 445 | 439 |
At | 12000 | 457 | 450 | 444 |
10,300 RPM | 34700 | 464 | --- | 451 |
Memorandum Report on
P-80A Airplane, AAF No. 44-85075
14 February 1947
A comparison has been made between the performance measured on P-80A airplane, AAF No. 44-85075, and that obtained on other P-80A airplanes tested by the Flight Test Division.
Representative examples of the best, the worst, and the average P-80A airplanes were used for this comparison.
All data presented had been corrected to a common take-off weight of 11,560 pounds and is for a P-80A airplane in the normal clean configuration.
The data has been plotted in Figure 6 and is given in tabular form as follows:
Maximum speed at 11,500 rpm at 11,560 pounds gross weight at take-off. |
Altitude | P-80A 44-85075 | P-80A 44-85044 #1 Engine | P-80A 44-85044 #2 Engine | P-80A 44-85123 | P-80A 44-85462 Unpainted |
5000 | 524 | 514 | --- | 548 | 525 |
20000 | 523 | 520 | 537 | 531 | 522 |
35000 | 490 | 507 | 512 | 500 | 502 |
Rate of climb (ft/min) at 11,500 rpm at 11,560 pounds gross weight at take-off.
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