Studies of Non-Linear Aerodynamic Characteristics of Finned Slender Bodies at High Angles of Attack.

摘要

This report describes both theoretical and experimental research performed on the subject of slender wing-body configurations at high angles of attack. The theoretical part of the research consists of a method for the computation of longitudinal aerodynamic characteristics of complex wing configurations at high angles of attack, and in subsonic flow including non-linear vortex lift caused by leading-edge or side-edge separations. The experimental part of the research consists of a study made on the effects of jets injected near the nose of a body, on the side forces and yawing moments appearing at high angles of attack at subsonic and transonic speeds. One of the main conclusions from the results of the experiments is that a great reduction of side-force and yawing moment can be achieved using small amounts of air injection by this method.