| 设计马赫数为5的一级二元混压式进气道典型状态下气动特性 |
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| 引用本文： | 翁小侪,郭荣伟,褚丹丹. 设计马赫数为5的一级二元混压式进气道典型状态下气动特性[J]. 航空动力学报, 2014, 29(9): 2040-2046. DOI: 10.13224/j.cnki.jasp.2014.09.004 |
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| 作者姓名： | 翁小侪 郭荣伟 褚丹丹 |
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| 作者单位： | 1. 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; |
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| 摘 要： | 对一种设计马赫数为5的一级二元混压式进气道再入大气层过程典型状态进行了仿真和风洞试验，得到了该进气道典型状态下的气动特性.结果表明:当来流马赫数高于设计马赫数（为5）时，进气道外压斜激波系提前汇合，与唇罩入射斜激波相互作用，产生了波-波干扰；尽管发生了流动分离，但当来流马赫数为7和6时进气道出口上游气流紊流度分别不超过3.337和3.256，且流道内动态压力信号的功率谱密度呈现白噪声特征，不会对发动机造成结构损伤.因此，对于宽来流马赫数工作范围的进气道来讲，为了提供足够的流量，可以适当降低进气道的设计马赫数.
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| 关 键 词： | 航空、航天推进系统 二元进气道 斜激波 流动分离 功率谱 |
| 收稿时间： | 2013-05-29 |
Aerodynamic characteristics of design Mach number of 5 two-dimensional inlet with mixed-compression under typical condition |
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| WENG Xiao-chai,GUO Rong-wei and ZHU Dan-dan. Aerodynamic characteristics of design Mach number of 5 two-dimensional inlet with mixed-compression under typical condition[J]. Journal of Aerospace Power, 2014, 29(9): 2040-2046. DOI: 10.13224/j.cnki.jasp.2014.09.004 |
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| Authors: | WENG Xiao-chai GUO Rong-wei ZHU Dan-dan |
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| Affiliation: | 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. Unit 94710, the Chinese People's Liberation Army, Wuxi Jiangsu 214141, China;3. Co-Innovation Center for Advanced Aero-Engine, Beijing 100191, China;4. Unit 94627, the Chinese People's Liberation Army, Wuxi Jiangsu 214141, China |
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| Abstract: | The aerodynamic characteristics of a design Mach number of 5 two-dimensional inlet with mixed-compression during reentry under typical condition were investigated experimentally using wind tunnel and simulation. The results show that: when the free stream Mach number is higher than the design Mach number of 5, the external ramp oblique shocks of inlet intersect in advance and impinge on the cow inner surface, causing shock-shock interaction in combination with the cow oblique shock. Though the flow separations occur, the turbulence intensities upstream the inlet exit are less than 3.337 and 3.256 respectively when the free stream Mach numbers are 7 and 6, and the power spetrum density of the dynamic pressure signals in the duct generally presents the characteristics of white noise, causing little damage to the structure of the engine. Accordingly, in order to improve the mass flow of the inlet working over a wide rang of free stream Mach number, the design Mach number of inlet can be reduced properly. |
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| Keywords: | aerospace propulsion system two-dimensional inlet oblique shock flow separation power spectrum |
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