三维高超声速边界层中eN方法的应用

针对e N方法中的鞍点法(SPM),结合内波理论,提出了一种简便算法.并用该算法计算了一个由平板、圆锥、圆柱3部分组成的模型以马赫数为10的速度在高度位于30~45km之间、攻角为0°和10°的工况下N值分布情况.结果表明:高度的增加会使转捩位置向下游移动,转捩面积会变小甚至消失;与攻角为0°相比,攻角为10°会使迎风的平板部分转捩发生的可能性增大,转捩面积也会变大;对于背风处的圆锥部分,攻角为10°却会减弱转捩发生可能性,使得转捩面积变小,甚至消失,而且转捩位置也会变化.

Application of eN method in three-dimensional hypersonic boundary layers

A simple algorithm of saddle-point method (SPM) in eN method was presented by using internal wave theory, and distribution of N was computed on a model made up of plate, cone and cylinder at the cases of 30-45 km altitudes, Mach number of 10, attack angles of 0° and 10°. The results and conclusions show that: as the altitude increases, the transition position moves downstream, and the transition area becomes smaller and even disappears. On the plate part (windward side), the transition possibility in 10° attack angle cases is bigger than that in 0° attack angle cases, and the transition area is larger too. But on the cone part (leeward side), the transition possibility in 10° attack angle cases is less, and the transition area is smaller, even inexistence. And the transition positions of these two series of cases are different.