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利用高阶紧致格式,采用直接数值模拟(DNS)和线性稳定性(LST)分析方法,对高超声速边界层的失稳机制和转捩特点进行了研究.通过对马赫数为6的2°攻角高超声速钝锥边界层的稳定性分析发现:小攻角高超声速钝锥边界层存在多枝不稳定模态;周向速度使钝锥的稳定性特征与不考虑周向速度时有本质的差别;转捩线在接近背风面处出现拐折现象是由失稳模态发生转换引起的.
The instability mechanism and transition characteristics of the hypersonic boundary layer are investigated by using the high-order compact format and direct numerical simulation (DNS) and linear stability analysis (LST) The analysis of the stability of hypersonic bluff cone boundary layer in the angle of attack shows that there exist many branches unstable modes in the hypersonic bluff cone boundary layer with small angle of attack. The circumferential velocity makes the stability characteristics of the blunt cone and the nature without the consideration of the circumferential velocity Of the difference; turn line near the leeward surface appear inflection phenomenon is caused by the instability mode conversion.