Investigations of Yawed Caret Wings in Hypersonic Range.

Results of investigations on yawed caret wings, carried out in a gun tunnel, are presented. The measurements comprised lateral force, yaw moment, static pressure distribution on the contour and Pitot pressure in the flow field for the determination of the shock system. Separation areas at the pressure side of the wing were determined by means of oil painting pictures. Measurements of velocity profiles in the boundary layer on the lower side of the unyawed wings showed only a weak influence of the pressure side bending. The derivatives of lateral motion determined from the measurements were compared with the tangential wedge theory and the two-dimensional theory by Bagley showing poor agreement between theory and measurement. However, good agreement between theory and measurement even in the case of large angles of incidence was obtained by assuming a modified pressure distribution in span direction. As all investigated wings proved to be laterally unstable, the influence of a rudder assembly on stability was roughly determined by means of the Newton method.