b.    The allowable maximum diving speed is not as great as desired for combat operations.

                 c.    At speeds above allowable diving speeds especially over twenty-thousand (20,000) feet, violent vibrations from tail buffeting are experienced.

                 d.    The maintenance difficulties experienced were greater than with any other standard type of American fighter.

                 e.    The subject aircraft is easy to fly. However, a longer period of time will be required for a pilot to become familiar with the operations and maximum performances of the aircraft than is required for a normal single engine fighter.

                 f.    The cockpit installations are crowded and not arranged in a specific orderly fashion.

                 g.    While the rate of climb is superior to all other types tested to date, this is not as great as required, especially below twenty-thousand (20,000) feet, and all excess weight in the structure and installations not vital to combat operations should be reduced or eliminated whenever possible.

                 h.    Cooling capacity of the intercooler is not sufficient to allow maximum horsepower to be extracted from the engine at altitude.

                 i.    The guns will not feed properly during maneuvers which create a pull of greater than 3-1/2 G’s.

                 a.    All conclusions and recommendations applying to the P-38F, apply to the P-38G.

                 b.    Inasmuch as the general maneuverability of this aircraft is probably the lowest of any type of current fighter aircraft, and in view of the competition facing the P-38G in the European Theatre, all possible effort should be made to improve its rate of climb and high speed.

                 c.    The P-38G turns much better than the P-38F (will close 180° in 360° circle) due to maneuver flaps.

                 d.    Buffeting was noticeable but at higher speeds and accelerations than in the P-38F.

                 e.    The P-38G will outzoom the P-38F.

                 f.    The P-38G will hold its altitude in turns at thirty-five-thousand (35,000) feet, whereas the P-38F loses altitude.

                 g.    The P-38G holds its advantages over the P-38F at all altitudes.

                 h.    The lack of sufficient intercooling holds down the performance of the P-38G as well as the P-38F.

       High speed and climb performance have been completed on this airplane at a take-off weight of 16,597 lb. This loading corresponds to athe average P-38 combat weight with full oil, 300 gallons of fuel and specified armament and ammunition.

       The principal results are as follows:

       The principal results are summarized in the following paragraphs.

       In level flight at 19800 ft., the critical altitude for 70" hg. manifold pressure, 3000 RPM, and 26,300 limiting turbo RPM, a maximum speed of 419 MPH was attained. At this altitude a high speed of 402.5 MPH was attained at 60" Hg. manifold pressure. At 24000 ft., the critical altitude for 60" Hg. manifold pressure, 3000 RPM, and 26,300 limiting turbo RPM, a high speed of 413 MPH was attained.

       At sea level a maximum rate of climb of 4040 ft/min was attained at 70" Hg. manifold pressure and a rate of climb of 3570 ft/min at 60" Hg. manifold pressure and 3000 RPM. The service ceiling of the airplane was 39,000 ft., and the absolute ceiling was 39,700 ft.

       Level Flight Performance

       The following speed data was obtained with the airplane in the clean configuration. Data is corrected to weight at altitude as given in Figure 4, Appendix A and NACA standard day conditions.

       a.    True speed at sea level at war emergency power, 1530 BHP and 3000 RPM, was 342 MPH.

       b.    True speed at critical altitude, 26,000 feet, at war emergency power, 1495 BHP and 3000 RPM, was 416 MPH.

       c.    True speed at sea level at military power, 1395 BHP and 3000 RPM, was 331 MPH.

       d.    True speed at critical altitude, 26,200 feet, at military power, 1385 BHP and 3000 RPM, was 408 MPH.

       e.    True speed at sea level at normal rated power, 1110 BHP and 2600 RPM, was 302 MPH.

       f.    True speed at critical altitude, 32,200 feet, at normal rated power, 1138 BHP, was 400 MPH.

Performance Characteristics of the P-38G-10 Airplane
P-38J Time to Bank 90°
Fighter Comparison Chart
P-38 Tactical Planning Characteristics & Performance Chart