Abstract
A numerical approach based on marching procedures is presented for three-dimensional supersonic flows involving shock-shock interactions, where the shock waves and the associated contact surfaces are determined as floating discontinuities in a fixed system of computational meshes. In order to calculate the regions having subsonic velocity components in the marching direction, which are embedded locally in a supersonic flowfield, a numerical method is also developed that is easily adaptable to the conventional marching procedures. The method consists of an alternate iteration of time-dependen t and marching schemes, in which an explicit finitedifference algorithm is employed to solve Euler's nonconservative equations. The results of complicated threedimensional flowfields about typical blunt-nosed wing/body combinations at angles of attack are presented to demonstrate the validity as well as the applicability of the present approach.
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