Shock interaction induced heat flux augmentation in hypersonic flows

Abstract This paper gives a summary of dedicated experiments on the shock interaction induced heat flux augmentation, by means tests carried out in hypersonic wind tunnel H2K. The first test case is devoted to boundary layer flat plate. impact has been varied changing free stream parameters and position generator, i.e. impingement point distribution determined using surface temperature data measured an infrared camera. combined with flow allow calculation Stanton number evolution. second double sphere configuration variable axial lateral distance between spheres. allowed measurements augmentation shock-shock along complete frontal sphere, which was hit bow sphere. Shock-shock shock-boundary effects are studied IXV flight control flaps. Depending parameters, factors up seven have measured. Graphical abstract