| 飞机/进气道一体化流场数值计算 |
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| 引用本文： | 郁新华,胡主根,黎先平.飞机/进气道一体化流场数值计算[J].洪都科技,2004(1):1-9. |
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| 作者姓名： | 郁新华 胡主根 黎先平 |
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| 作者单位： | 洪都航空工业集团650所 |
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| 摘 要： | 对飞机进气道组合体进行了粘性流场的数值模拟,通过求解N-S方程并建立合理的边界条件来模拟不同飞行速度(亚、超音速)、不同攻角和发动机流量下的进气道性能,给出了进气道进口局部马赫数、攻角和侧滑角的分布以及进气道的总压恢复情况。
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| 关 键 词： | 飞机 进气道 N-S方程 数值计算 |
| 修稿时间： | 2004年2月17日 |
Calculation of Integral Flow Field of Aircraft/Air Inlet |
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| Yu Xinhua Nanerical Hu Zhugen Li Xianping.Calculation of Integral Flow Field of Aircraft/Air Inlet[J].Hongdu Science and Technology,2004(1):1-9. |
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| Authors: | Yu Xinhua Nanerical Hu Zhugen Li Xianping |
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| Institution: | Hongdu Aviation Industry Group |
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| Abstract: | The numerical simulation of viscosity flow field on an assembled unit of aircraft air inlet,simulation of the performances of air inlet at different flight speeds (subsonic, supersonic), angle of attacks, and engine air flow, thriugh the result of N-S equation and establishment of the proper boundary condition are the ways to find the local Mach number,angle ofattack,the distribution of sideslip angle at the intake of air inlet and total pressure recovery condition of air inlet. |
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| Keywords: | Aircraft Air inlet N-S equation Numerical calculation |
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