3-D Navier-Stokes analysis of crossing, glancing shocks/turbulent boundary layer interactionsThree dimensional viscous flow analysis is performed for a configuration where two crossing and glancing shocks interact with a turbulent boundary layer. A time marching 3-D full Navier-Stokes code, called PARC3D, is used to compute the flow field, and the solution is compared to the experimental data obtained at the NASA Lewis Research Center's 1 x 1 ft supersonic wind tunnel facility. The study is carried out as part of the continuing code assessment program in support of the generic hypersonic research at NASA Lewis. Detailed comparisons of static pressure fields and oil flow patterns are made with the corresponding solution on the wall containing the shock/boundary layer interaction in an effort to validate the code for hypersonic inlet applications.
Document ID
19910059008
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Reddy, D. R. (NASA Lewis Research Center Cleveland, OH, United States)