Application of NPLS Technique to Hypersonic Shock-Wave and Boundary Layer Interactions

Abstract

While flying with hypersonic speed, the aircraft vehicle will produce very strong shock wave. The interactions between shock wave and boundary layer not only increase the drag, but also produce high pressure and high aerodynamic heating. The shock wave oscillation usually appears in the inlet of engine and in the flow inside the high-speed turbine, and this phenomena can cause unsteady heating, and excite various kinds of unsteady modes to result in tired material destroy. Therefore, it is very essential to strengthen the study and set up the effective estimate or prediction method of shock wave and boundary layer interactions.