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利用有限体积法对轴对称可压缩的N S方程进行离散 ,对喷嘴的超声速垂直冲击射流进行了数值模拟。网格的划分采用非结构性网格 ,湍流模型为S A湍流模型 ,在近壁处采用壁面函数进行修正。分别计算压比为3和 4的超声速欠膨胀垂直冲击射流 ,得到详细的波系结构 ,激波形状和位置与实验相吻合。大压比下 ,壁面上冲击中心区域压力相对低 ,分布较平坦 ,压力最大点所在位置偏离中心冲击点 ,并且在近壁处有回流
The finite-volume method is used to discretize the axially symmetric and compressible N S equation, and the supersonic vertical impinging jet of the nozzle is numerically simulated. Mesh is divided into unstructured grids. The turbulence model is S A turbulence model, and the wall function is used to modify the near wall. The supersonic superselective vertical impinging jets with pressure ratios of 3 and 4 were calculated respectively, and the detailed wave structure was obtained. The shape and location of the shock wave coincided with the experiment. Under high pressure ratio, the pressure in the center of the impact area is relatively low and the distribution is relatively flat. The location where the maximum pressure is located deviates from the center impact point, and there is reflux at the near wall