侧压式进气道与飞行器机体气动一体化设计及实验

Experiment of aerodynamic performance for hypersonicvehicle integrated with sidewall compression inlet

以机体 推进系统耦合、三维侧压式进气道为基本特征,设计了采用超燃冲压发动机为推进系统的高超声速一体化冷流通气实验模型,在高超声速炮风洞中完成了飞行器的整体气动测力试验。在来流马赫数Ma=8.09的条件下,分别测定了飞行器结合单模块、3模块、5模块超燃冲压发动机在-4°～6°六个攻角下模型的气动力数据,并对实验结果作了分析。

A hypersonic vehicle integrated with propulsion model is designed. Three dimension side compression inlet and scramjet were used. The aerodynamics force performance wind tunnel test of the model with none module, 1 module, 3 modules and 5 modules scramjet is finished in KD-01 hypersonic gun wind tunnel.Experimental data is measured when free Mach number is 8.09 and angle of attack is between -4° and 6°. The results were analyzed.