An analysis is made of the effects of Mach number and dynamic pressure on the lift-curve slope of a large flexible swept-wing jet-propelled airplane by using flight measurements of normal acceleration and angle of attack with auxiliary instrumentation as needed. The methods and procedures used to correct the flight measurements (obtained in abrupt push-pull maneuvers) and to convert the flight test data to equivalent rigid conditions for comparison with rigid-model wind-tunnel tests are described in detail. The airplane angle of zero lift and the airplane-less-tail angle of zero lift for the Mach number range of the flight tests (0.42 to 0.81) are also presented. Excellent agreement was obtained in the comparison between flight and wind-tunnel rigid lift-curve slopes and angles of zero lift.

A theoretical analysis was made to investigate the performance and acceleration-restriction capabilities of a normal-acceleration command control system in a fighter airplane. Several combinations of pitching velocity and pitching acceleration were investigated as feedback quantities in combination with normal acceleration.

Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.