Numerical Study of 2D Curved Shock Wave Turbulent Boundary Layer Interaction

Abstract

The shock wave boundary layer interaction (SWBLI) due to curved shock is studied prominently, as most military aircrafts and missiles undergo strong SWTBLI due to its curved or blunt shape. These interactions effect the performance of vehicles at supersonic flow regime. The present numerical study investigates, interaction between a shock wave and turbulent boundary layer (SWTBLI) for cylindrical shock generators at freestream Mach number 3. The diameter (D) of cylindrical shock generator is varied to determine the effect of strength of shock on boundary layer and effect on impinging location from leading edge of flat plate, which depends upon the position of cylindrical shock generator. Two dimensional numerical simulations are carried out on mentioned model using commercially available CFD solver that employs k-omega SST turbulence model. Computational results show a good agreement qualitatively in terms of separation location and separation bubble length and quantitatively predicts the surface pressure, accurately as compared to the experiments conducted by literature.

Keywords

• shock wave
• shock wave/boundary layer interaction
• diameter of cylinder
• boundary layer
• separation bubble and surface pressure