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为分析前缘钝化对高超声速二元进气道压缩面边界层转捩的影响,针对抽象出的楔面外形,在风洞来流条件下,应用线性稳定性理论(Linear Steady Theory)分析了前缘钝化半径R=0及R=0.5mm的楔面边界层流动稳定性,得到各自前缘构形的边界层失稳位置及最不稳定波的波数和增长率。研究发现,前缘钝化半径R=0.5mm的楔面边界层失稳位置远远大于前缘钝化半径R=0的楔面边界层失稳位置,表明前缘钝化对楔面边界层失稳特性具有显著影响。
In order to analyze the influence of leading edge passivation on the boundary layer transition of the hypersonic binary inlet compression plane, aiming at the abstract wedge shape, under the conditions of wind tunnel flow, the linear stability theory (Linear Steady Theory) The flow stability of the wedge boundary layer with leading passivation radius R = 0 and R = 0.5 mm was obtained, and the instability position of the boundary layer and the wave number and growth rate of the most unstable wave were obtained. It is found that the instability position of the wedge boundary layer with the leading edge passivation radius R = 0.5mm is far greater than the wedge boundary instability position with the leading edge passivation radius R = 0, indicating that the leading edge passivation affects the wedge boundary layer Unstable characteristics have a significant effect.