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为深入探究唇罩侧板后掠对二元高超声速进气道起动性能的影响规律,采用风洞试验与三维数值模拟分析相结合的方法,对比分析了侧板不同后掠状态下的不起动流场特征,细致地研究了后掠角度影响进气道起动的流动机理。研究结果表明:唇罩后掠能够提高进气道的起动能力,来流Ma=5.0和Ma=4.0时,进气道的最小起动后掠角分别为75°和82.5°。Ma=5.0来流条件下,不起动的分离包前缘形态在一定范围内基本不受后掠角影响。唇罩后掠角度增大时主要通过侧板的展向溢流,改变分离包的位置及形态,进而通过降低分离包内的逆压梯度来影响进气道的起动性能。
In order to further study the influence law of lip flaps swept to the start-up performance of binary hypersonic air intake, wind tunnel test and three-dimensional numerical simulation are used to analyze the non-start Flow field characteristics, detailed study of the sweep angle of the inlet flow of the start of the flow mechanism. The results show that the lip sweep can improve the starting ability of the inlet, and the minimum starting swept angle of inlet is 75 ° and 82.5 ° respectively when the flow Ma = 5.0 and Ma = 4.0. Under the condition of Ma = 5.0, the shape of the leading edge of the non-activated separation bag is not affected by the sweep-back angle within a certain range. When the sweep angle of the lip cap increases, the position and shape of the separation bag are changed mainly by the spanwise expansion of the side panels, which in turn affects the starting performance of the intake duct by reducing the pressure gradient in the separation bag.