WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEED OF THE STATIC LONGITUDINAL STABILITY CHARACTERISTICS OF AnWINGED REENTRY VEHICLE HAVING A LARGE NEGATIVELYnDEFLECTED FLAP-TYPE CONTROL SURFACE

摘要

An investigation has been made in the Langley high-speed 7- by 10-foot tunnel to determine the feasibility of using a flap-type control surface to provide longitudinal trim and stability throughout an angle-of-attack range from -2° to 90° on a clipped-delta-wing configuration, having an aspect ratio of 1.12, a taper ratio of 0.29, and a leading-edge sweep angle of 63°, considered for reentry from satellite orbit. The model was tested at Mach numbers- from 0.60 to 0.90 with correspondingnReynolds numbers of 2.76 x 10° to 4.03 x 10° based on the basic-wing mean aerodynamic chord. The control surface consisted of a large trailing-edge flap that extended outboard of the wing tips. Vertical tails attached to the control surface at the wing-tip station moved with the control surface.nThe control arrangement provided longitudinal trim and stability over most of the angle-of-attack range. However, the configuration was unstable at angles of attack from approximately 12° to 2k°, especially at the lower Mach numbers.