矩形截面高超声速进气道高焓风洞实验

袁化成; 郭荣伟

矩形截面高超声速进气道高焓风洞实验

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2010-01-24
- 修回日期: 2010-06-10
- 刊出日期: 2010-12-28

High enthalpy wind tunnel tests of hypersonic inlets with rectangular section

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

摘要

摘要: 对设计工作马赫数为4.5~6.5的矩形截面高超声速进气道进行了马赫数为6,5及4的高焓风洞实验研究,获得了进气道在不同反压下的性能参数及沿程静压分布.实验结果显示,设计状态下(Ma=6,α=0°),进气道的流量系数和总压恢复系数分别为0.97和0.41,增压比约为来流静压的35倍,隔离段出口马赫数不大于2.6;最大承受反压不小于来流静压的114.5倍.研究还发现,反压升高引起的激波串可停留在内压段,且不影响进气道的流量捕获;当Ma=5,α=0°时,进气道的流量系数不低于0.77,总压恢复系数在0.49~0.67之间.设计工作马赫数及攻角范围内,进气道内未发现明显的流动分离,均可正常起动工作.
- 高超声速进气道 /
- 二元进气道 /
- 矩形截面 /
- 高焓风洞实验 /
- 马赫数 /
- 攻角
Abstract: Preliminary test study was conducted for hypersonic inlets with rectangular section at Mach number of 6,5 and 4 in a high enthalpy wind tunnel.The inlet could be started within the range of the Mach number 4.5 and 6.5.The performance and static-pressure distributions of the inlet under different back-pressure conditions were obtained.Results indicate that,at design condition(Ma=6,α=0°),the mass flow capture rate and mass-averaged total pressure recovery coefficient are 0.97 and 0.41,respectively;at the exit section of the isolator,the average Mach number is less than 2.6,the pressure rise and maximum back-pressure are 35 and 141.52 times of upstream pressure.The shock train formed by back-pressure rising can be kept in the inner tunnel,without affecting the mass flow capture rate.The mass flow capture rate is not less than 0.77,and the mass-averaged total pressure recovery coefficient varies between 0.49 and 0.67 at Mach number of 5 and 0° angle of attack.In the non-back-pressure status,there is no obvious flow separation in the flow inlet field of the inlet.
- hypersonic inlet /
- two-dimensional inlet /
- rectangular section /

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参考文献(14)

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