内压缩通道几何参数对高超声速进气道性能的影响

Performance Effects of Geometry Parameters on Hypersonic Inlet

用N-S方程模拟了一系列不同收缩比、不同波系配置的内压缩通道内流动,研究了内压收缩通道几何参数对进气道性能的影响,发现对于相同的外压段,内压面积收缩比对进气道内压缩通道温升比、压比和起动性能具有较好的相似规律,且随着内压面积收缩比增加,进气道温升比、压比增加,出口流场畸变下降,起动马赫数增大。通过对相同压比下不同内外压缩比的进气道性能的研究,得到了内外压缩比对进气道效率和起动性能的影响规律,发现压缩程度相同时,进气道效率和起动马赫数均随内外压缩比有先增大后减小再增大的规律。

A series of inner contraction tunnels with different contraction area ratios and different shocks are designed. The flows are simulated with N-S equation and performance effects of the geometry parameters on the hypersonic inlet are investigated. The contraction area ratio can be used to design a hypersonic inlet. With the increase of the contraction area ratio, the temperature and the pressure ratios increase, the total pressure distortion decreases and the starting Mach number increases. For different models, with same outer contraction parts, rules of the temperature ratio, the pressure ratio and the starting Maeh number with the contraction area ratio are all similar. Inlets with the same pressure ratio and different pressure ratios between the inner channel and the outer compression system （IOPR） are investigated and effects of IOPR on the inlet efficiency and the starting Maeh number are founded： the inlet efficiency and the starting Mach number increase firstly, decrease secondly and then increase, finally they are balanced in the design.