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为研究前缘钝度及模型尺度对流场结构的影响,采用了长度为0.3 m和0.6 m的三级压缩楔模型,前缘半径分别为0,0.5,1,1.5,3 mm,在0.6 m激波风洞中利用高速阴影摄像获得了系列流场结构照片,清晰地显示了激波结构。试验条件为马赫数5.98,总温670 K,总压6.56MPa。数据结果表明,随着前缘半径的增加,第一道激波角增大,第二和第三道激波角减小;存在明显的模型尺度影响,在同等钝度条件下(尖前缘除外),两个尺度模型的第一道激波角相差迭0.4°,第二道和第三道激波角最大可相差0.5°。流场照片显示,在拐角处存在激波边界层干扰,造成第二、三道激波根部弯曲,随前缘半径增加,弯曲程度和影响区域增大。
In order to study the influence of frontal dullness and model scale on the flow field structure, a three-stage compression wedge model with length of 0.3 m and 0.6 m was used. The leading edge radii were 0, 0.5, 1, 1.5 and 3 mm, respectively. m shock wave wind tunnel using high-speed shadow camera to obtain a series of photos of the flow field structure, clearly shows the shock wave structure. The test conditions were Mach 5.98, total temperature 670 K, total pressure 6.56 MPa. The results show that with the increase of the radius of the leading edge, the first shock angle increases and the second and third shock angles decrease. There is a significant model scale effect. Under the same obtuse condition Except that the first shock angle of the two scale models differs by 0.4 ° and the second and third shock angles can differ by a maximum of 0.5 °. The flow field photographs show that the shock wave boundary layer interferes at the corner, causing the root of the second and third shocks to bend. As the radius of the leading edge increases, the bending degree and the area of influence increase.