| 在激波边界层干扰中后掠柱形区的独立性原理研究 |
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| 引用本文： | 邓学蓥 Sett.,GS.在激波边界层干扰中后掠柱形区的独立性原理研究[J].空气动力学学报,1989,7(4):442-448. |
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| 作者姓名： | 邓学蓥 Sett. GS |
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| 作者单位： | 北京航空航天大学
(邓学蓥)，美国Princeton大学(G.S.Settles) |
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| 摘 要： | 在后掠压缩角引起的三维激波边界层干扰中,柱形的上游影响区表现出准二维的流动特性。实验结果表明,在柱形区中通常的边界层独立性原理不再适用。但是,如果考虑由后掠引起的横流效应修正,柱形区中的上游影响距离的尺度和相应的二维干扰上游影响区尺度之间可以得到很好的相关关系。
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| 关 键 词： | 激波 边界层 柱形 干扰 |
A TEST OF THE INDEPENDENCE PRINCIPLE IN SWEPT CYLINDRICAL SHOCK WAVE/TURBULENT BOUNDARY LAYER INTERACTIONS |
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| Deng Xueying.A TEST OF THE INDEPENDENCE PRINCIPLE IN SWEPT CYLINDRICAL SHOCK WAVE/TURBULENT BOUNDARY LAYER INTERACTIONS[J].Acta Aerodynamica Sinica,1989,7(4):442-448. |
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| Authors: | Deng Xueying |
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| Abstract: | The cylindrical upstream influence region in the three dimensional interactions between shock wave and turbulent boundary layer induced by swept com-pression corner appears quasi two dimensional flow behaviors. The results show that the independence principle can not apply to the cylindrical region. However, if the effects of cross flow are considered, a good correlation of upstream influence scale between cylindrical interaction and two dimensional interaction can be obtained. |
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| Keywords: | shock wave three dimensional boundary layer |
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