Supersonic Flow past Conical Bodies at Large Angles of Attack

概要

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In order to solve the supersonic flow around a conical body with a large angle of attack by the inviscid equations, in such a flow the viscous effect of the separation region at the leeward side of the body being very important, the new concept of the equivalent body is introduced. The equivalent body consists of the original body at the windward side and an additional conical body at the leeward side which is expanded in proportion to the increase of the angle of attack. This additional conical body exhibits approximately the viscous effect of the separation region. What the "lift off" parameter of the vortical singularity κ is equal to -8 at the leeward generator of the equivalent body is used as the criterion which determines the dimensions of the equivalent body. By employing this concept, the supersonic flow around conical bodies can be calculated up to the angle of attack of twice as large as the semi apex angle of the conical body. And the results obtained by the present method show in good agreement with the experiments and the usefulness of this method is confirmed.
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