Numerical Simulation of Vortical Flows over Fighter Configuration with Euler Equations
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摘要: 用三步显式格式时间推进求解物理空间曲线网格上有限体积离散的Euler方程, 数值模拟一种战斗机外形的涡流场. 计算的机翼表面压力分布与实验符合较好, 用Euler方程捕获到机翼前缘分离涡( 主涡) 及翼面上的二次分离涡. Euler方程解中出现的二次涡可能是逆压梯度、尖锐边缘和人工粘性共同作用的结果, 它的流谱与实验定性符合.Abstract: A three-stage explicit scheme is used for time-stepping solutions of Euler equations discretized in physical curvilinear grid cell of finite volume simulating vortical flows over a generic fighter configuration. The predicted pressure distribution on wing surface is in good agreement with experiments. The primary vortex from leading edge of wing as well as the secondary vortex on upper wing surface is captured. The secondary vortex in the solution of Euler equations is attributed to the combined effect of adverse pressure gradient, sharp edge and artificial viscosity, and the flow picture of the secondary vortex is qualitatively similar to that of experimental observation.
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Key words:
- fighter /
- vortex flow /
- Euler motion equations /
- finite volume method /
- secondary vortex
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