高超声速边界层感受性问题高精度数值模拟  

High-order accuracy numerical simulation of hypersonic boundary receptivity problems

作　　者：李建华[1] 王强[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2008年第4期532-537,共6页Acta Aerodynamica Sinica

摘　　要：通过五阶WENO格式和六阶对称紧致格式以及三阶TVD R-K结合的方法,对存在强激波和小扰动相互干扰的高超声速边界层感受性问题进行研究。结果表明:此方法能够模拟边界层内不稳定波的产生和发展以及小扰动和激波相互干扰等现象,因此能广泛应用于含激波的感受性等问题的可压缩湍流直接数值模拟以及具有激波和边界层干扰等复杂流场的计算。A numerical method which combines five-order WENO scheme, six-order symmetric compact difference scheme and three-order TVD Runge-Kutta is used to solve the Navier-Stokes equations for the simulation of hypersonic boundary receptivity exiting interaction between strong shock wave and weak disturbance wave. The results correctly display T-S traveling within the boundary-layer and interaction phenomenon between weak wave and shock wave. These results also indicate the method is applicable to DNS （Direct Numerical Simulation） of receptivity problems containing shock wake and complex flow field simulation exiting interaction between shockwave and turbulent boundary laver.

关 键 词：WENO格式 直接数值模拟 感受性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]