论文部分内容阅读
采用分区方法及Roe三阶流通量差分分裂格式求解雷诺平均N－S方程，湍流附加黏性系数用Baldwin－Lomax模型计算，数值模拟了高超声速条件下变高度圆柱诱导的激波边界层干扰，其流场的主要特性均与实验结果一致或规律相同，结果清晰地展示了流场结构以及气动载荷分布随柱高度的变化特征，并说明激波碰撞和旋涡运动都可能导致飞行器表面局部气动载荷的增加．
Reynolds averaged N-S equation was solved by the partition method and Roe third-order flux difference splitting scheme. The additional turbulent viscosity coefficient was calculated by Baldwin-Lomax model, and the shock boundary layer disturbance induced by the variable height cylinder was numerically simulated. The main characteristics of the flow field are consistent with the experimental results or the same law. The results clearly show that the flow field structure and the aerodynamic load distribution with the height of the column changes, and that both shock shock and vortex motions may lead to local aerodynamic loads on the aircraft surface Increase.