THE FLAPS AND WING LEADING EDGE

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONNASA MEMO IO-II-58LAERODYNAMIC CHARACTERISTICS IN SIDESLIP OF ALARGE-SCA_ 49° SWEPTBACK WING-BODY-TAILCONFIGURATION WITH BLOWING APPLIED OVERTHE FLAPS AND WING LEADING EDGE*By H. Clyde McLemoreSUMMARYAn investigation has been conducted in the Langley full-scale tun-nel to determine the aerodynamic characteristics in sideslip of a large-scale 49° sweptback wing-body-tail configuration having wing leading-edge and flap-blowing boundary-layer control. The wing and tails hadan aspect ratio of 3.5, a taper ratio of 0.3, and NACA 65A006 airfoilsections parallel to the plane of symmetry. The tests were conductedover a range of angles of attack of about -5° to 28° for sideslip anglesof 0°, -5.06 °, -10.15 °, and -15.18 °. Lateral and longitudinal stabilityand control characteristics were obtained for a minimized blowing rate.The Reynolds number of the tests was 5.2 X 106 , corresponding to a Machnumber of 0.08.The results of the investigation showed that sideslip to angles ofabout -15° did not require, from a consideration of the longitudinalcharacteristics, blowing rates over the wing leading edge or flap greaterthan that established as minimum at zero sideslip. The optimum con-figurationwas laterally and directionally stable through the completelift-coefficient range including the stall; however, maximum lift forsideslip angles greater than about 5° was seriously limited by a defi-ciency of lateral control. Blowing over the leading edge of the retreatingwing in sideslip at a rate greater than that established as minimum atzero sideslip was ineffective in improving the lateral control character-istics. The optimum configuration at zero sideslip had no hysteresisof the aerodynamic parameters upon recovery from stall.*Title, Unclassified.