FLIGHT EVALUATION OF ANGLE OF ATTACK AS A CONTROL PARAMETER IN GENERAL-AVIATION AIRCRAFT

Abstract The use of angle-of-attack information for a pilot's display in a general-aviation airplane was investigated to determine whether this form of information would improve performance and flight safety. An angle-of- unit, and a display instrument was installed and flight tested in a typical attack system consisting of a wing-mounted vane, an electronic computer twin-engine, general-aviation airplane, The flight-test maneuvers were limited to the low-speed flight region where the benefits of angle-of-attack presentation were likely to be greatest. Some of the expected advantages of this parameter, such as visual indication of stall margin and its inde- pendence of gross weight and flap position, were realized: however. certain aerodynamic characteristics of the airplane. such as the phugoid and directional-control capability, were found to limit and tended to negate some of the expected advantages.