Effects of wall cooling on performance parameters of hypersonic inlets
Effects of wall cooling on performance parameters of hypersonic inlets
复制标题
壁面冷却对高超声速进气道性能参数的影响
DOI：
10.1016/j.actaastro.2009.02.005
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发表时间：
2009-08
影响因子：
3.5
通讯作者：
Fan, Yi
中科院分区：
文献类型：
--
作者：
Bao, Wen;Yu, Daren;Chang, Juntao;Shen, Yi;Fan, Yi
对二维混合压缩高超声速进气道在不同壁面温度下的内部流场进行了数值模拟。讨论了壁面冷却对无背压和有背压高超声速进气道性能参数的影响，特别是对固定几何形状高超声速进气道最大背压的影响。分析了壁面冷却提高高超声速进气道最大背压的内部物理机制。与无壁面冷却相比，无背压的高超声速进气道静压比略有降低，但在壁面冷却的作用下，质量捕获系数、总压恢复系数和隔振器出口处的流动均匀性都有所提高。壁面冷却减弱了边界层与激波的相互作用，使得隔振器入口处由高背压引起的边界层分离发生较晚，提高了高超声速进气道的最大背压比。随着壁面温度的降低，增加了最大背压比和质量捕获系数，降低了高超声速进气道的总压恢复系数。
The internal flowfield of a 2-D mixed-compression hypersonic inlet was simulated numerically at different wall temperatures. The effects of wall cooling on performance parameters of the hypersonic inlet without and with the backpressure, and especially on the maximum backpressure of a fixed-geometry hypersonic inlet were discussed. The inner physical mechanism of wall cooling improving the maximum backpressure of hypersonic inlets was analyzed. In contrast with no wall cooling, the static pressure ratio of hypersonic inlets without backpressure is reduced slightly, but the mass-captured coefficient, total-pressure recovery coefficient and the flow uniformity of hypersonic inlets at the isolator exit are improved by the action of wall cooling. The interaction between boundary layers and shocks is weakened due to wall cooling, which leads to that the boundary layers separations at the entrance of the isolator caused by the high backpressure occur later, and it can improve the maximum backpressure ratio of hypersonic inlets. With the wall temperatures decreasing, the maximum backpressure ratio and mass-captured coefficient are added, and the total-pressure recovery coefficient of hypersonic inlets is reduced.
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DOI：
10.1017/s0001924000002505
发表时间：
2008-09
期刊：
The Aeronautical Journal (1968)
影响因子：
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期刊：
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影响因子：
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DOI：
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发表时间：
2006-07
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DOI：
10.2514/6.2001-1818
发表时间：
2001-04
期刊：
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影响因子：
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作者：
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