乘波体构型飞行器的高超声速测压实验研究  

Experimental study on aerodynamic characteristics of a hypersonic waverider configuration

作　　者：肖虹[1] 高超[1] 党云卿[2] 

机构地区：[1]西北工业大学翼型/叶栅空气动力学国家科技重点实验室,西安710072 [2]中航工业第一飞机设计研究院,西安710089

出　　处：《实验流体力学》2011年第3期34-36,40,共4页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金项目(10572115)

摘　　要：乘波体构型是高超声速飞行器的重要气动布局之一。对某多目标优化设计的乘波体构型飞行器进行了高超声速测压实验,对其气动性能进行风洞实验验证。实验马赫数M=6和M=7,迎角α=-4°-、2°、0°、2°、4°、6°、8°。结果表明:该乘波体构型各部件气动性能良好。进气道唇口准确捕捉到压缩激波,激波位置与设计吻合。乘波体上表面流向压力变化不大,有利于减小乘波体飞行阻力。下表面经过进气口内压段时压力有明显的增大,后体膨胀效果显著。在设计状态下,该乘波体飞行器整体气动性能良好。The waverider configuration is an important configuration of hypersonic cruise vehicle. Hypersonic flow around a multi-objective optimization designed waverider is experimentally studied by pressure measurement, force measurement and Schlieren observation at M= 6 and 7 and angle of attack ranging from -4° to 8°. The results show that the aerodynamic characteristics of all the components of the waverider are good. The forebody precompression quality meets the design requirements well, the forebody shock is exactly caught by the lip of the inlet and the flow is quickly expanded at the aft body.

关 键 词：乘波体 气动特性 测压试验 高超声速 激波 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]