| 蛇形进气道涡控设计研究 |
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| 引用本文： | 谢文忠,郭荣伟. 蛇形进气道涡控设计研究[J]. 航空学报, 2011, 32(10): 1806-1814. DOI: 11-1929/V.20110426.1122.007 |
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| 作者姓名： | 谢文忠 郭荣伟 |
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| 作者单位： | 南京航空航天大学能源与动力学院,江苏南京,210016 |
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| 基金项目： | 国家自然科学基金(11002069); 南京航空航天大学青年科技创新基金(NS2010051)~~ |
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| 摘 要： | 针对传统概念设计的蛇形进气道畸变大、总压恢复系数较低以及相应流场控制技术存在局限性等缺点,对典型蛇形进气道内通道二次流的涡动力学形成及其对气流分离影响分析的基础上,提出了蛇形进气道涡控设计概念,并利用数值仿真进行了初步验证.仿真结果表明:与原型方案相比,蛇形进气道涡控设计方案成功抑制了上壁面大范围的气流分离,巡航状态畸...
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| 关 键 词： | 航空航天推进系统 蛇形进气道 涡控设计概念 涡动力学 流向涡 二次流 气流分离 |
| 收稿时间： | 2010-12-22; |
Vortex-controlled Design Research for Serpentine Inlet |
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| XIE Wenzhong,GUO Rongwei. Vortex-controlled Design Research for Serpentine Inlet[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(10): 1806-1814. DOI: 11-1929/V.20110426.1122.007 |
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| Authors: | XIE Wenzhong GUO Rongwei |
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| Affiliation: | XIE Wenzhong,GUO Rongwei College of Energy & Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China |
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| Abstract: | To deal with the low total pressure recovery rate and the high distortion level of serpentine inlets designed with the traditional method,a novel design concept of serpentine inlets based on surface vortex controlled global secondary flow reconstruction is presented in this paper.The simulation validation for the concept shows that:1) the vortex-controlled model successfully alleviates the large separation occurring on the top surface of the baseline model,which is because the vortex induced by the vortex-c... |
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| Keywords: | aerospace propulsion system serpentine inlet vortex-controlled design concept vortex dynamics streamwise vorticity secondary flow flow separation |
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