Shock wave boundary layer interaction at high flap angles and high incidence of space vehicles in hypersonic flow

An experimental study has been carried out to study the shock wave boundary layer interaction and its impact on the aerodynamics of a hypersonic flight configuration. Tests have been carried out in the hypersonic wind tunnel H2K of the German Aerospace Center in a broad range of incidence and flap angle with a particular focus on the high angle case. A model made of carbon reinforced plastic was used for the tests. The low thermal conductivity allowed simultaneous surface temperature measurements using an IR camera parallel to force measurements. Additionally Schlieren and oil flow techniques were applied to visualize the flow around the model and the constant shear stress topology on the model surface. It has been noticed that at certain combinations of angle of attack and flap angle the shock configuration on the flaps changes completely. All four measurement techniques, i.e. force measurements, IR thermography, oil flow visualization and Schlieren pictures confirmed this result and thus clearly confirmed the influence of the shock boundary layer interaction on the flap efficiency and the pitching moment behavior of the vehicle