Instability and Transition Prediction of Stationary Crossflow Vortices Over Supersonic Swept Elliptic Cylinders
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摘要: 实验发现,一定条件下超声速后掠圆柱的前半圆上可能发生定常涡引起的转捩.为了模拟高空超音速飞行器后掠翼前缘,以无限展向长度后掠椭圆柱为模型,基于eN方法,根据积分的N值,分析了迎风轴长度、Reynolds(雷诺)数、后掠角和Mach(马赫)数等参数的变化对超音速后掠椭圆柱横流定常涡不稳定性的影响.研究结果表明,后掠椭圆柱的迎风轴长度增加,会使横流定常涡的不稳定性增强;Reynolds数增大,使横流定常涡模态的不稳定性增强;不稳定性的强度与Reynolds数的大小为近似线性关系;飞行高度增加,Mach数变大,使横流定常涡的不稳定性变弱;后掠角在一定范围内的变化对横流定常涡的不稳定性影响不大.这些结果有助于提高对高空超音速飞行器翼前缘转捩机理的认识,为横流转捩预测提供理论指导Abstract: Some experiments had shown that stationary crossflow vortices may cause transition over the 1st halves of supersonic swept cylinders. The swept elliptic cylinders with infinite spanwise lengths were used to simulate the swept wings of supersonic aircrafts at high altitudes. Based on the eN method and the N factor, the influence of changing the parameters including the upwind axis length, the Reynolds number, the swept angle and the Mach number on the instability of the stationary crossflow vortices over supersonic infinite swept elliptic cylinders was studied. The results show that, the instability of stationary crossflow vortices is stronger with longer upwind axes or larger Reynolds numbers. Meanwhile, the relationship between the instability of stationary crossflow vortices and the Reynolds number is almost linear. The results also show that the stationary crossflow vortices are more stable in the conditions with greater Mach numbers. The change of the swept angle in a certain range has a small effect on the instability of stationary crossflow vortices. These results would be helpful to improve the understanding of the transition mechanism over the leading edges of supersonic aircraft wings and provide theoretical guidance for crossflow transition prediction.
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