翼付半円錐物体まわりの非粘性極超音速流の研究

抄録

The steady hypersonic flow around a slender conical flat-top wing-body has been solved by applying the equivalence principle, which is the theory that the problem of steady hypersonic flow past a slender body is equivalent to the problem of unsteady flow in a plane. Then, the problem of this conical flat-top wing-body becomes into the problem of an expanding motion of a hemi-cylinder with a plane wing. The flowfield of this expanding body has successfully been solved by means of a conformal transformation and a superposition technique. Moreover, the other problems of small angles of attack, vortices, shock shape etc. have been also solved. As for the experimental investigation, the flow around the expanding body has been visualized. The experimental results agree well with the theoretical ones.