| 一种战斗机外形涡流场Euler方程数值模拟 |
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| 引用本文： | 张正科.一种战斗机外形涡流场Euler方程数值模拟[J].北京航空航天大学学报,1998,24(2):233-236. |
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| 作者姓名： | 张正科 |
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| 作者单位： | 北京航空航天大学宇航学院，北京航空航天大学飞行器设计与应用力学系 |
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| 基金项目： | 国家自然科学基金和博士后科学基金资助项目 |
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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.
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| 关 键 词： | 战斗机 涡流 Euler运动方程 有限体积法 二次涡 |
| 收稿时间： | 1996-09-02 |
Numerical Simulation of Vortical Flows over Fighter Configuration with Euler Equations |
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| Zhang Zhengke,Zhu Ziqiang,Zhuang Fenggan.Numerical Simulation of Vortical Flows over Fighter Configuration with Euler Equations[J].Journal of Beijing University of Aeronautics and Astronautics,1998,24(2):233-236. |
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| Authors: | Zhang Zhengke Zhu Ziqiang Zhuang Fenggan |
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| Institution: | 1. Beijing University of Aeronautics and Astronautics,School of Astronautics;
2. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics |
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| Abstract: | A threestage explicit scheme is used for timestepping 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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| Keywords: | fighter vortex flow Euler motion equations finite volume method secondary vortex |
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