3-D NAVIER-STOKES ANALYSIS OF CROSSING GLANCING SHOCKS TURBULENT BOUNDARY-LAYER INTERACTIONS

Three-dimensional viscous Row analysis is performed for a configuratio n where two crossing and glancing shocks interact with a turbulent bou ndary layer. A time marching 3-D full Navier-Stokes code, called PARC3 D, is used to compute the flow field and the solution is compared to t he experimental data obtained at the NASA Lewis Research Center 1 ft x 1 ft supersonic wind tunnel facility. The study is carried out as par t of the continuing code assessment program in support of the Generic Hypersonic Research at NASA Lewis. Detailed comparison of static press ure fields and oil flow patterns is made with the corresponding soluti on on the wall containing the shock/boundary layer interaction in an e ffort to validate the code for hypersonic inlet applications.