| 超声速翼—身组合体Euler方程数值解 |
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| 引用本文： | 陈万春,纪楚群.超声速翼—身组合体Euler方程数值解[J].空气动力学学报,1992,10(2):210-217. |
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| 作者姓名： | 陈万春 纪楚群 |
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| 作者单位： | 北京航空航天大学，北京航空航天大学，北京空气动力研究所 北京 100083，北京 100083，北京 100074 |
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| 摘 要： | 本文采用MacCormack二步显式差分格式,用空向推进法给出了超声速翼-身组合体Euler方程的数值解。应用薄翼假设生成简易的多区网格。采用Kentzer方案处理边界。计算中通过对横流速度型的修正改善了背风面压力分布特性,解决了推进中断问题,同时模拟出背风涡。
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| 关 键 词： | 超声速流 数值计算 翼－身组合体 |
Euler Solution for Wing-body Combination at Supersonic Speeds |
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| Chen Wanchun Yang Zhenshen.Euler Solution for Wing-body Combination at Supersonic Speeds[J].Acta Aerodynamica Sinica,1992,10(2):210-217. |
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| Authors: | Chen Wanchun Yang Zhenshen |
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| Institution: | Chen Wanchun Yang Zhenshen (Beijing university of Aeronautics and Astronautics)Ji Chuqun (Beijing Institute of Aeronautics) |
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| Abstract: | Space marching methods are used here to solve the Euler equations of a wing-body configuration at supersonic speeds by MacCor-mack's scheme. The thin-fin approximation is employed to generate the computational grid. Kentzer's approach is used to treat boundaries. By modifying the crossflow velocity profiles for the consideration of viscous effects, the leeside surface pressure distributions are improved considerably, flow separation is formed in the leeside region in the meantime, computational interruption problem caused by numerical oscillations are solved successfully as a result. |
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| Keywords: | supersonic flow numerical calculation wing-body combination numerical oscillation separation |
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