| 一种宽马赫数变几何超声速进气道气动性能研究 |
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| 引用本文： | 赵昊,谢旅荣,郭荣伟,王建勇,张骏.一种宽马赫数变几何超声速进气道气动性能研究[J].航空动力学报,2015,30(7):1678-1684. |
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| 作者姓名： | 赵昊 谢旅荣 郭荣伟 王建勇 张骏 |
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| 作者单位： | 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;中国航空工业集团公司 中国航空动力机械研究所, 湖南 株洲 412002;先进航空发动机协同创新中心, 北京 100191,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191,中国航空工业集团公司 中国航空动力机械研究所, 湖南 株洲 412002 |
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| 基金项目： | 国家自然科学基金(11302101) |
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| 摘 要： | 为了改善二元宽马赫数超声速进气道非设计点下的气动性能,设计了一种来流马赫数为2.0~4.5的变几何超声速进气道,对其气动性能开展了数值仿真研究,得出了性能较优的变几何方案,并与相应的定几何进气道进行了对比.研究结果表明:采用变几何方法可提高进气道在转级点的气动性能;随着来流马赫数的增大而增加进气道的楔角及内收缩比,可降低进气道的喉道马赫数;采用该变几何方法可有效提高进气道宽工作范围的气动性能,在某些状态下流量系数和总压恢复系数比定几何进气道分别高出19.4%和55.8%.
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| 关 键 词： | 超声速进气道 变几何进气道 楔角 宽马赫数 气动性能 |
| 收稿时间： | 2014/1/16 0:00:00 |
Study of variable geometry supersonic inlet aerodynamic performance in a wide Mach number range |
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| ZHAO Hao,XIE L&#;-rong,GUO Rong-wei,WANG Jian-yong and ZHANG Jun.Study of variable geometry supersonic inlet aerodynamic performance in a wide Mach number range[J].Journal of Aerospace Power,2015,30(7):1678-1684. |
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| Authors: | ZHAO Hao XIE L&#;-rong GUO Rong-wei WANG Jian-yong and ZHANG Jun |
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| Institution: | Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China,Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China,Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China and China Aviation Powerplant Research Institute, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China |
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| Abstract: | In order to improve the off-design aerodynamic performance of supersonic inlet, a two-dimensional variable geometry inlet with the free stream Mach number from 2.0-4.5 was designed. Numerical simulation was applied to investigate the inlet aerodynamic performance, and a superior scheme of variable geometry was acquired. The aerodynamic performance was compared between variable geometry inlets and fixed ones. The results indicate that the variable geometry technique could improve the inlet aerodynamic performance at the starting Mach number; Mach number at the throat of variable geometry inlet decreases with the increase of the inlet ramp angle and contraction ratio when the free stream Mach number ascends. The variable geometry inlet has better aerodynamic performance during a wide range of Mach number, its mass flow rate and total pressure recovery coefficient are 19.4% and 55.8% respectively higher than the fixed ones in some states. |
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| Keywords: | supersonic inlet variable geometry inlet ramp angle wide Mach number aerodynamic performance |
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