Numerical simulation of shock/turbulent boundary layer interactions over 2-D compression corners

A computational study of shock wave/turbulent boundary layer interactions over two dimensional compression corners at Mach 3 is presented. The Baldwin-Lomax turbulence model for two dimensional, supersonic interactions was investigated. A general purpose computer code was developed for the numerical solution of the two dimensional compressible Reynolds averaged Navier-Stokes equations, with turbulence represented by an algebraic eddy viscosity model. The developed Navier-Stokes computer code was successfully validated by application to a variety of test cases including inviscid shocked flows, laminar and turbulent boundary layers, and shock/laminar boundary layer interactions. Compressions ramp flowfields were simulated using the Navier-Stokes equations together with three different versions of the Baldwin-Lomax turbulence model, including the incorporation of a relaxation technique. The turbulence models were evaluated by a detailed comparison with available experimental data for compression ramp flows at Mach 3 and over a range of corner angle and Reynolds number. All of the turbulence models tested fail to simulate the rapid recovery of the boundary layer downstream of reattachment.