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为了探索模型缩尺比对高超声速进气道气动性能的影响,对不同缩尺比的二元高超声速进气道开展了数值模拟研究,结果表明:随着缩尺比的增大,进气道流量系数、隔离段出口总压恢复系数和马赫数均逐渐增大,而静压比逐渐减小,且来流马赫数越高,上述参数变化幅度越大。由理论与数值模拟分析可知,上述现象主要是由于不同缩尺比下,进气道当地雷诺数不同,导致进气道附面层相对厚度变化,进而影响进气道气动性能。理论分析了进气道总压恢复系数与缩尺比的定量关系,就进气道而言,进气道进口处附面层相对厚度减小1%,隔离段出口总压恢复系数提高约0.7%。
In order to explore the influence of the model scale ratio on the aerodynamic performance of the hypersonic inlet, the numerical simulation of the binary hypersonic inlet with different scale ratios was carried out. The results show that with the increase of the scale ratio, Road flow coefficient, the total pressure recovery factor and the Mach number at the exit of the isolation section are gradually increased, while the static pressure ratio is gradually reduced, and the higher the Mach number, the greater the range of the above parameters. The theoretical and numerical simulation shows that the above phenomenon is mainly due to the different local Reynolds number of the inlet, resulting in the relative thickness change of the inlet, thus affecting the aerodynamic performance of the inlet. The quantitative relationship between the total pressure recovery coefficient and the scale ratio is theoretically analyzed. As for the inlet, the relative thickness of the inlet at the inlet decreases by 1%, and the total pressure recovery at the outlet of the isolation section increases by about 0.7 %.