The propulsion and airframe integration structure is commonly used on aerodynamic configuration of hypersonic vehicle. The shock waves generated by the front face of the aircraft are quite different whether the inlet is open or closed under hypersonic flow condition, which have a significant impact on the air rudders and the engine inlet, causing great change of the aerodynamic stability of the aircraft. In this paper, based on the principle of forced oscillation dynamic derivative technique, a new method for the dynamic derivatives test of a lifting body model with internal and external flow in high speed wind tunnel is developed. The research mainly includes the establishment of dynamic derivatives test system, model support system, model inlet flow simulation method and so forth. The results show that the model combined with the method of tail support can effectively simulate the flow conditions, and increasing the ventilation channel height appropriately can better meet the requirements of hypersonic flow simulation.
展开▼
