其他摘要：The principal objective of this paper is to study hypersonic viscous flows dominated by shock-wave / laminar boundary-layer interaction over a compression corner. The shock-wave / boundary-layer interaction is studied using numerical solution of the Navier-Stokes equations for unsteady flows using a Mach number equal to 10.30. The flows are simulated using the Finite Element Method with two explicit Taylor-Galerkin schemes with linear tetrahedral and tri-linear hexahedral elements. Results include surface pressure, skin friction and velocity/pressure/density profiles in several stations.
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