| 超声速进气道在亚临界条件下的附加阻力的计算 |
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| 引用本文： | 周建华,董金钟,黄熙君,李欣. 超声速进气道在亚临界条件下的附加阻力的计算[J]. 航空发动机, 2002, 0(3): 42-46 |
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| 作者姓名： | 周建华 董金钟 黄熙君 李欣 |
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| 作者单位： | 北京航空航天大学,北京,100083 |
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| 摘 要： | 以二波系轴对称外压式超声进气道为例,说明进气道在亚临界工作状态下的脱体激波位置和附加阻力系数的英美计算方法及俄罗斯的附加阻力系数计算方法,两种方法的计算结果与实验数据的比较表明了该算法的有效性,并对两种算法的特点进行了比较和分析。
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| 关 键 词： | 超声速进气道 附加阻力 亚临界条件 计算 |
| 修稿时间： | 2002-02-23 |
Calculation of Additive Drag of Supersonic Inlet under Subcritical Operating Condition |
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| Zhou Jianhua Dong Jinzhong Huang Xijun Li Xin. Calculation of Additive Drag of Supersonic Inlet under Subcritical Operating Condition[J]. Aeroengine, 2002, 0(3): 42-46 |
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| Authors: | Zhou Jianhua Dong Jinzhong Huang Xijun Li Xin |
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| Abstract: | UK and US calculating methods of detached shock wave position and additive drag coefficient, for the example of axisymmetric supersonic inlet, are introduced under subcritical operating condition and Russian method of additive drag coefficient is also provided in the paper. The results have shown that the methods are validated. In addition, the methods are contrastively analyzed. |
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| Keywords: | supersonic inlet additive drag subcritical operating condition calculation |
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