Experimental and Numerical Study of Shock-Wave Boundary Layer Interactions on an Axisymmetric Body

摘要

An experimental and numerical study of shock-wave boundary layer interactions on a tangent ogive cylinder body has been carried out at Mach 2 flow conditions. Experiments were conducted in the polysonic wind tunnel at the Florida State University. Measurements include shadowgraph and surface oil flow visualizations, force and moments using a six-component strain gage balance. Numerical simulations were conduced using Kestrel multi-physics flow solver. The results show that the aerodynamic characteristics of an axisymmetric body are significantly altered in the presence of shock impingement on its surface. The location and strength of shock affect its lift and pitching moment characteristics. Numerical simulations provide detailed features of this complex flow field involving shock-shock and shock-boundary layer interactions.