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Shock-Boundary layer interaction in shock tube (Reynolds 200) -

This is an unsteady viscous computation of a shock tube problem in a closed 1x1 box. The initial conditions are set with two gases at rest, same temperature but pressure and density ratio of 100 (left over right values). The Reynolds number (200) is based on the initial speed of sound and the box length. This test case has been proposed by Daru and Tenaud.

Due to the initial pressure discontinuity, a shock wave travels from left to right while accelerating the flow and creating a boundary layer on the bottom wall. Then the shock hits the right wall, crosses the initial gas interface and travels back to the left. The shock wave makes the boundary layer separate into a complex vortical flow.

Schilieren-like of R200 Shock-Boundary layer interaction (400x200)
400x200 mesh
HLLC scheme, MUSCL extrapolation


Schilieren-like of R200 Shock-Boundary layer interaction (800x400)
800x400 mesh
HLLC scheme, MUSCL extrapolation


Schilieren-like of R200 Shock-Boundary layer interaction (1600x800)
1600x800 mesh
HLLC scheme, MUSCL extrapolation