| 双下侧布局带泄流腔二元进气道试验 |
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| 引用本文： | 麻肖妃,谢旅荣,郭荣伟.双下侧布局带泄流腔二元进气道试验[J].航空动力学报,2010,25(8):1818-1824. |
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| 作者姓名： | 麻肖妃 谢旅荣 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,南京,210016 |
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| 摘 要： | 针对一种双下侧布局带泄流腔的二元进气道进行了试验研究.试验时,来流速度范围Ma=2.0~3.5,姿态角范围为α=-4°~10°,β=0°~4°.试验获得了进气道的反压特性曲线、速度特性曲线、迎角特性曲线和侧滑角特性曲线.分析表明,随着来流速度和迎角的增加,进气道的流量系数先增加,在设计点达到最大,之后由于弹身头部激波的影响略有减小.侧滑时两侧进气道气流状态不同,工作范围由性能较低的迎风侧进气道来决定.另外,通过分析进气道的沿程静压分布曲线,说明泄流腔结构能使结尾激波停留在泄流腔边缘,扩大了进气道的工作范围.
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| 关 键 词： | 冲压发动机 超声速进气道 泄流腔 风洞试验 混压式 |
| 收稿时间： | 7/7/2009 12:00:00 AM |
| 修稿时间： | 2009/11/30 0:00:00 |
Investigation of two-dimensional supersonic twin inlet with slot-coupled cavity in 90°configuration at venter |
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| MA Xiao-fei,XIE Lü-rong,GUO Rong-wei.Investigation of two-dimensional supersonic twin inlet with slot-coupled cavity in 90°configuration at venter[J].Journal of Aerospace Power,2010,25(8):1818-1824. |
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| Authors: | MA Xiao-fei XIE Lü-rong GUO Rong-wei |
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| Affiliation: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | A two-dimensional mixed-compression inlet model with slot-coupled cavity in 90° configuration at venter was investigated by wind tunnel at Mach number from 2.0 to 3.5.The range of the investigation covers angle of attack from-4° to 10° and angle of yaw from 0 to 4°.The performances,including critical pressure,total pressure recovery coefficient and mass flow ratio,were acquired.The results indicate that:with increase of the free stream Mach number or the angle of attack at Ma=3.0,the mass flow ratio increases firstly and then declines a little due to the increase of the total pressure loss around the body nose;and the maximum is obtained at design point.The flow field of two inlets is different at yaw,and the work range is determined by the windward inlet.Besides,the distribution of static-pressure coefficient along the duct validates that a terminal shock can stay around the cavity,so inlets with the slot-coupled cavity can work under wider back pressure. |
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| Keywords: | ramjet engine supersonic inlet slot-coupled cavity wind tunnel test mixed-compression |
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