Numerical simulations of oblique Shock- wave turbulent boundary- layer interaction on flat plate using GAO- YONG compressible turbulence equations are presented. This paper presents two cases with different incident shock angles, 15. 876°and 23. 287°with the same free- stream Mach number 5. 0 which induce attached and detached flows. Convection terms and diffusion terms are calculated using ROE scheme and CD ( center difference) scheme respectively. The Runge - Kutta time marching method is employed to solve space discrete control equations. Typical flow features of Shock- wave turbulent boundary -layer interaction are described well in simulation. Meanwhile, calculations accurately predict distribution of pressure on flat plate,skin friction number and Stanton number. Good agreements between the calculations and experiment are obtained.%应用GAO-YONG可压缩湍流方程组数值模拟了入射斜激波/平板湍流边界层相互干扰现象,计算了来流马赫教为5 0,激波入射角度分别为15.876°、23 287.两种不同激波干扰强度下的流场.计算程序中的对流项、扩散项分别采用二阶ROE格式和二阶中心差分格式离散,并用多步Runge-Kutta显式时间推进法求解空间离散后的控制方程.计算较好地模拟了高马赫数下的激波/湍流边界层干扰的流场结构,位移边界层厚度,动量损失厚度等,也比较准确地预测了平板壁面压力、摩阻系数等气动力参数的分布.
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