FULL-SCALE WIND-TUNNEL TESTS OF A LOW-ASPECT-RATIO, STRAIGHT-WING AIRPLANE WITH BLOWING BOUNDARY-LAYER CONTROL ON LEADING- AND TRAILING-EDGE FLAPS

摘要

A full-scale wind-tunnel investigation was made to determine the effects of boundary-layer control on the leading- and trailing-edge flaps of a fighter-type airplane having a thin, upswept, low-aspect-ratio wing.nIt was found that, with the leading- and trailing-edge flaps deflected 45°, the application of boundary-layer control resulted in significant increases in maximum lift, aileron effectiveness, and longitudinal stability at high angles of attack. With the leading-edge flaps deflected 30°, the only appreciable effect of applying boundary-layer control to the leading-edge flap was to increase the aileron effectiveness between angles of attack of 15° and 19°. It was also determined that the air-flow requirements of the boundary-layer control systems were well within the capabilities of the compressor bleed-air system of the turbojet engine used in the airplane.