Study of aerodynamic performance for integrated hypersonic vehicle's scaled model in the nonuniform flow fields of wind tunnel

The most significant challenge in the research of airbreathing hypersonic vehicle is to predict the aero-propulsive performance precisely.In this paper,the wind tunnel experimental model of integrated hypersonic vehicle designed by AHL(Airbreathing Hypersonic Laboratory) of CARDC is investigated with numerical method.The flow fields of 600mm impulse combustion wind tunnel of CARDC are studied numerically and compared with the experimental results.The reasonable installed position of experimental model is presented.The aerodynamic performance of the un-powered(inlet open but engine not working) model with attack angle and rudders is studied.The effects induced by the parts of model not put entirety in the uniform flow fields of the wind tunnel are also simulated and presented.These results provide the important evidences for analyzing the aerodynamic performance of vehicle precisely according to wind tunnel experimental results.