LOW-SPEED WIND-TUNNEL INVESTIGATION OF BLOWINGnBOUNDARY-LAYER CONTROL ON LEADING- AND TRAILING-EDGE FLAPS OF A FULL-SCALE, LOW-ASPECT-RATIO, 42° SWEPT-WING AIRPLANE CONFIGURATION

摘要

A wind-tunnel investigation was made on a complete full-scale model having a thin, low-aspect-ratio, 42° sweptback wing with single- and double-droop leading-edge flaps and trailing-edge flaps, both equipped with blowing boundary-layer control (BLC). Lift, drag, pitching-moment, and rolling-moment data were measured for an angle-of-attack range from -8° through stall at a Reynolds number of 8.1 million.nThe effects of leading-edge flap deflection and blowing BLC on lift and the delay of leading-edge flow separation were generally similar to those reported in previous investigations (NACA RM A58A09 and NASA MEMO 1-23-59A) for wings of similar sweep and aspect ratio. These effects should be qualitatively applicable to other models of similar wing plan form.