宽马赫数范围高超声速进气道转动唇口变几何方案研究

结合简单一维流理论讨论了一种工作于Ma=4～7、采用可转动唇口的变几何二元高超声速进气道设计方案,并利用数值仿真手段对其Ma=4下的自起动性能及其他不同工作马赫数下的性能进行了研究.结果表明:所设计的变几何进气道必须辅以附面层排移措施才能在Ma=4下顺利实现自起动;该变几何方案Ma=4下的流量系数达0.7以上,这为飞行器加速提供了强有力保障;与定几何进气道相比,变几何进气道高低马赫数下的总体性能均得到显著提高;此外,转动唇口的铰接位置对自起动性能有重要影响.

Investigation of a variable geometry scramjet inlet with a rotating cowl operating in a large Mach number range

A simple variable geometry scramjet inlet with a rotating cowl operating in a large Mach number range from 4 to 7 was designed.During the inlet design,one-dimensional flow theory was used to distribute the internal and external compressions.The inlet self-starting characteristics at Ma=4 and the global performance at different incoming Mach numbers were studied by means of numerical simulations.Results indicate:(1) Inlet's self-start can be realized successfully at Ma=4 under the help of the boundary layer diverter placed at the entrance of the cowl section.(2) Variable geometry inlet achieves a mass capture ratio of 70 percent at the starting Mach number,which is very favorable to the acceleration of the hypersonic vehicles.(3) Global performance parameters of the variable geometry inlet are greatly increased in the whole operating range compared with the fixed geometry inlet.(4) Position of the cowl rotation axis has a great effect on the inlet self-starting characteristic.