| 低速发动机短舱压强分布计算 |
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| 引用本文： | 陈炳永,曾明,朱自强,张炳暄.低速发动机短舱压强分布计算[J].航空学报,1993,14(6):299-302. |
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| 作者姓名： | 陈炳永 曾明 朱自强 张炳暄 |
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| 作者单位： | 北京航空航天大学流体力学研究所,北京 100083 |
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| 基金项目： | 上海民用飞机技术研究中心部分资助 |
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| 摘 要： | 应用第二代面元法对发动机短舱的压强分布进行了计算。计算结果表明其精确度与第一代高阶面元法相当;并可避免第一代面元法计算内流时出现的“泄漏”(leakage)问题。该方法具有节省机时和便于复杂外形应用的特点。
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| 关 键 词： | 面元法 发动机短舱 不可压流动 |
| 收稿时间： | 1991-12-29 |
| 修稿时间： | 1992-06-24 |
CALCULATION OF THE PRESSURE DISTRIBUTION ON THE NACELLE IN LOW SPEED |
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| Chen Bing-yong,Zeng Ming,Zhu Zi-qiang,Chang Bing-xuan.CALCULATION OF THE PRESSURE DISTRIBUTION ON THE NACELLE IN LOW SPEED[J].Acta Aeronautica et Astronautica Sinica,1993,14(6):299-302. |
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| Authors: | Chen Bing-yong Zeng Ming Zhu Zi-qiang Chang Bing-xuan |
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| Institution: | Institute of Fluid Mechanics, Beijing University of Aeronautics and Astronautics, Beijing, 100083 |
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| Abstract: | In the process of aerodynamic design, the panel method is one of the main computing tools. In this paper the second generation low order panel method is used for calculation of the pressure distribution on the nacelle in low speed. It is demonstrated that the present low order method gives comparable accuracy to the result of high order panel method, It is excellent compared with some earlier low order methods, e.g. "the leakage" in internal flows calculation does not appear with the present method. Meanwhile, the computing cost of the method is very low and it is very easy for application to complex configurations. |
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| Keywords: | panel method nacelle incompressible flow |
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