NASA NTRS · 19810031496
Thin-layer approximation for three-dimensional supersonic corner flows
Abstract
The thin-layer approximation is extended to an axial corner that is formed by the intersection of two perpendicular plates, one of which has an inclination angle with respect to the free stream. A computer code developed by Hung and MacCormack (1978) is modified for the thin-layer approximation, and a case with Mach 5.9 and a wedge angle of 6 deg is computed. In addition, it is shown that it is not necessary to solve the complete Navier-Stokes equations for a three-dimensional high-Reynolds-number corner flow.
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Hung, C. M., Kurasaki, S. S.. 1980-12-01. Thin-layer approximation for three-dimensional supersonic corner flows. https://ntrs.nasa.gov/citations/19810031496
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