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Shock-Induced Large Separation Bubbles Near the Leading Edge of a Flat Plate at Hypersonic Mach Numbers

机译:高超声速马赫数的平板前缘附近的激振引起的大分离气泡

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An experimental study of the impinging shock boundary layer interaction was carried out at Mach number of 5.88, stagnation enthalpy of 1.26 MJ/kg and Reynolds number based on plate length of 0.769 million. The influence of the leading edge bluntness on the interaction was studied. It was found that the separation length had a maximum value for the sharp leading edge, while it had nearly constant value for the 2 and 4 mm blunt leading edge. The reattachment pressure also followed the same trend, suggesting the weakening of the impinging shock caused by the bluntness. Numerical simulations did not predict the separation lengths accurately. However, it was able to predict the trend qualitatively.
机译:基于板长7.69百万,在5.88马赫数,1.26 MJ / kg的停滞焓和雷诺数下进行了撞击冲击边界层相互作用的实验研究。研究了前沿钝化对交互的影响。发现分离长度对于锋利的前缘具有最大值,而对于2mm和4mm钝的前缘具有几乎恒定的值。重新安装的压力也遵循相同的趋势,这表明钝器造成的冲击力减弱了。数值模拟不能准确预测分离长度。但是,它能够定性地预测趋势。

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