Studies of hypersonic viscous interaction

Based on the similarity solution for hypersonic boundary layers, correlative analyses for viscous interaction effect are conducted with numerical method, curves of the wall pressure on the surfaces of the effective body vs the local effective angle of attack and the viscous interactive parameter are presented. The conclusion is that the difference between the wall pressure on the surfaces of the effective body and the real body is proportional to the viscous interactive parameter at bigger local effective angle of attack. Hypersonic flow fields around a liftbody configuration are numerically simulated, the numerical results validated the code and displayed the good agreement with the conclusion of correlative analyses.