Shock/Turbulent Boundary Layer Interactions
The shock wave/turbulent boundary interaction exists for all supersonic or hypersonic vehicles. In this research, the 3D Reynolds averaged Navier-Stokes equations with full Reynolds stress transport equation model are solved to simulate the shock wave/turbulent boundary layer interaction caused by asymmetric crossing shock waves at Mach number 4.0. The pressure distribution agrees well with the experiment, but the heat transfer coefficient largely deviates from the experiment. More advanced turbulent boundary layer simulation such as large eddy simulation or direct numerical simulation are needed to improve the prediction accuracy.
- Zha, G.-C., and Knight, D. D., " Computation of 3D Shock/Turbulent Boundary Layer Interaction Using a Reynolds Stress Equation Turbulence Model", AIAA Journal, Vol. 34, No.7, July 1996, p. 1313-1320
- Gnedin, M., Zha, G.-C., Knight, D. D., Zheltovodov, A., Maksimov, A., Shevchenko, A., and Vorontsov, S, "3-D Asymmetric and Symmetric Crossing Shock Wave-Turbulent Boundary Layer Interaction", International Conference on Methods of Aerophysical Research, Novosibirsk, Russia, Sept. 1996
- Zha, G.-C. and Knight, D. D., " Computation of 3D Asymmetric Crossing Shock Wave/Turbulent Boundary Layer Interaction Using a Full Reynolds Stress Equation Turbulence Model", AIAA Paper 96-0040, 1996, 34th Aerospace Sciences Meeting \& Exhibit, Jan. 15-18, 1996