Numerical Simulation Research Of Boundary And Shock Wave Interaction Over Ramp

Shock wave and boundary layer interaction is an important physical phenomenon. It widely exists in the interior and exterior flow field of all kinds of hyper-velocity vehicles. When this interaction phenomenon occurs, the local aerodynamic heat of the vehicles can be greatly intensified, which may change the aerodynamic load and increase the resistance and cause the inlet gas mass loss and so on. When the shock wave is strong enough, in particular, the boundary layer separation may happen earlier and consequently a very complex shock wave structure forms nearby the separation area. This shock wave structure has important influences to the stability characteristics of the boundary layer. Therefore, it has been an important issue to understand the complex shock wave and boundary layer interaction in the development of hypersonic/supersonic vehicles.In this thesis a numerical analysis on the shock wave boundary layer interaction is carried out, where a hypersonic inlet flow over a three dimensional ramp on a plate is considered. The surface pressure distribution and the complex shock wave structure due to the interaction of the boundary layer and the shock wave generated by the leading edge and the ramp are studied in detail. Four different ramp angles namely 10°, 20°, 30°and 40°are computed, and the Mach number and the inlet flow unit Reynold's number is fixed at 8 and 7.05×106/m respectively.First for the shock wave and the boundary-layer theories, deduce scalar artificial viscosity centered discretization scheme,the upwind Van Leer difference scheme for supersonic flow simulation including from basic fluid conservation equation;Then use the preprocessor CFD-GEOM to generate computation model, use computational fluid dynamics software CFD-FASTRAN to solve the computation model, which select the proper boundary condition and initial condition;Last in order to get the basic interaction shock wave structure in detail, the rule of distribution of pressure,temperature,viscosity coefficient,stress, analyze the computational results of velocity fields;...