P-80 Performance Trials

Flight Test Division Memorandum
Report Serial No. TSFTE-2009
26 August 1946

Performance Tests on the Lockheed
P-80 A-1 Airplane, AAF No. 44-85044

Summary

        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-11Serial No. 006137
Engine No. 2 - J-33-GE-11Serial No. 006112
Engine No. 3 - J-33-A-9Serial 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 Level510-----494
10,000518-----512
20,000520-----513
25,000519534507
30,000515526497
35,000507512485
40,000495-----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.
CleanTip TanksCleanTip Tanks

Sea Level46403300     0     0
10,00037302510  2.4  3.4
20,00028301720  5.5  8.2
30,0001910925  9.816.4
40,000  400----19.0----

For more of this report see HERE


Air Material Command
Wright Field, Dayton, Ohio

Memorandum Report on
The P-80A-5LO Airplane, AAF No. 44-85462
7 November 1946

Summary

        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  5,000526533536
at 11,50020,000521528530
 34,000504505505

Cruising True Airspeed  5,000421426429
at 10,40020,000434442445
 34,000431439444

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Air Material Command
Wright Field, Dayton, Ohio

Memorandum Report on
The P-80A-1, AAF No. 44-85123
3 December 1946

Summary

        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  2700562556548
True Airspeed  7600561554546
At12000557550542
11,500 RPM34700505---501

Cruising  2700445439435
True Airspeed  7600452445439
At12000457450444
10,300 RPM34700464---451

For more of this report see HERE


Air Material Command
Wright Field, Dayton, Ohio

Memorandum Report on
P-80A Airplane, AAF No. 44-85075
14 February 1947

Summary

        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.


AltitudeP-80A
44-85075
P-80A
44-85044
#1 Engine
P-80A
44-85044
#2 Engine
P-80A
44-85123
P-80A
44-85462
Unpainted

  5000524514---548525
20000523520537531522
35000490507512500502

                Rate of climb (ft/min) at 11,500 rpm at 11,560 pounds gross weight at take-off.


AltitudeP-80A
44-85075
P-80A
44-85044
#1 Engine
P-80A
44-85044
#2 Engine
XP-80A
44-83201
 

  50003900380044004100 
200002500240031002800 
1500140020001800 

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Supplemental

P-80A 44-85077, Speed vs Altitude, Painted
P-80A 44-85077, Speed vs Altitude, Surface Filler
P-80A 44-85077, Speed vs Altitude, Surface Configuration Comparison
Pilot's Flight Operating Instructions for P-80A-1 Airplane

WWII Aircraft Performance