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主要进行了超燃冲压发动机三面压缩进气道的实验观测。利用来流马赫数4.5的直通式激波风洞,考察了三组具有不同压缩角度的进气道模型内部的流场情况。实验观测手段为油流法、丝线法和高速纹影,同时,辅以数值模拟以有助于流场细节分析。纹影照片展示了进气道内部以激波边界层相互作用为主要影响因素的流场复杂结构,数值模拟也显示了相近的结果。油流技术与丝线法显示了近壁面处的流动图像,照片中可见激波、分离线、再附线等分界线位置。根据实验结果,可以推测唇口激波与进气道内边界层的相互作用及其引起的壁面分离是影响进气道内流动的主要因素。同时,尝试了利用抽吸方法减弱激波与边界层相互作用诱发的壁面流动分离,并取得一定结果。
Mainly carried out scramjet engine three-sided compression inlet experimental observation. Using the straight-through shock wind tunnel with Mach 4.5, the flow field inside the three intake manifold models with different compression angles was investigated. Experimental methods for oil flow method, silk method and high-speed grain, at the same time, supplemented by numerical simulation to help flow detail analysis. Squint photos show the complex structure of the flow field with the interaction of the shock boundary layer in the inlet and the numerical simulation also show similar results. Oil flow technology and silk method shows the flow near the wall of the image, the photo can be seen in the shock, the separation line, re-attached lines and other boundaries. According to the experimental results, it can be inferred that the interaction between the lip shock and the inlet boundary layer and the wall separation caused by it are the main factors affecting the in-port flow. At the same time, attempts to attenuate the wall-flow separation induced by the interaction between the shock wave and the boundary layer by using the suction method have been made and certain results have been obtained.