高超声速二元变几何进气道气动方案设计与调节规律研究

 针对二元高超声速进气道宽马赫数大攻角工作要求,研究了转动唇口变几何进气道调节方案,给出了一种高性能变几何原型进气道设计方法,并通过数值仿真获得了变几何进气道各工况下的调节规律及性能变化规律。研究表明:采用特殊曲面唇口设计的变几何进气道宽马赫数范围内流场结构较好,总体性能优越;以马赫数Ma=6.0为设计点的原型进气道采用转动唇口方案无需附面层抽吸即可在唇口开启过程中实现接力点自起动,且最低自起动马赫数降至Ma=3.5;低马赫数大攻角状态下,通过转动唇口合理控制喉部平均马赫数范围可保证进气道正常工作。

Design and Regulation of Two-dimensional Variable Geometry Hypersonic Inlets

A variable geometry inlet with a rotating cowl operating in a large Mach number range with large angles of attack is studied through numerical simulation, which yields a design method of the baseline variable geometry inlet with high performance and a law of performance variation and regulation under different conditions. The result shows that: the variable geometry inlet with curved cowl has better performance and flow field structure in the large Mach number range. The variable geometry inlet designed at Mach number Ma=6.0 with a rotating cowl can realize self-start at Ma=4.0 without the boundary layer diverter, and the lowest Mach number of self-start is Ma=3.5. The cowl can maintain the normal working of the inlet by rotating properly to control the average Mach number of the throat at low incoming Mach numbers with large angles of attack.