| 引用本文: | 刘伟.带控制舵机动弹头粘性绕流数值模拟.[J].国防科技大学学报,2002,24(3):1-3.[点击复制] |
| LIU Wei.Numerical Simulation of Viscous Flows over Maneuvering Missile with the Control Helm[J].Journal of National University of Defense Technology,2002,24(3):1-3[点击复制] |
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| 带控制舵机动弹头粘性绕流数值模拟 |
| 刘伟 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 采用空间二阶精度的交替方向隐式分解的NND格式求解完全气体假定下的非定常薄层近似Navier-Stokes方程，并采用抛物化的椭圆型方程生成复杂带翼外形的空间网格。最后给出带控制舵机动弹头在M∞=7.3，α=20°下所计算的流场等值线、表面压强分布及表面极限流线。 |
| 关键词: 机动弹头 高超声速流动 数值模拟 Navier-Stokes方程 极限流线 |
| DOI： |
| 投稿日期：2001-12-05 |
| 基金项目:国家部委基金资助项目(413130101)；湖南省自然科学基金资助项目(01JJY2008) |
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| Numerical Simulation of Viscous Flows over Maneuvering Missile with the Control Helm |
| LIU Wei |
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(College of Aerospace and Materials Engineering,National Univ. of Defense Technology,Changsha 410073,China)
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| Abstract: |
| Under the assumption of perfect gas，the thin layer N-S equations are solved by alternating direction implicit NND scheme，and the space grids of complex wing-shape are generated by solving parabolic partial differential equations. Finally，the numerical simulation results of maneuvering missile with the control helm are shown under the conditions:M∞=7.3，α=20°.The results include contours of flow-field, pressure distribution and limiting streamline along the surface. |
| Keywords: maneuvering missile hypersonic flow numerical simulation Navier-Stokes equations limiting steamline |
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