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矩形截面高超声速进气道高焓风洞实验
引用本文:袁化成,郭荣伟.矩形截面高超声速进气道高焓风洞实验[J].航空动力学报,2010,25(12):2748-2755.
作者姓名:袁化成  郭荣伟
作者单位:南京航空航天大学能源与动力学院,南京,210016
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.

关 键 词:高超声速进气道  矩形截面  风洞实验
收稿时间:2010/1/24 0:00:00
修稿时间:2010/6/10 0:00:00

High enthalpy wind tunnel tests of hypersonic inlets with rectangular section
YUAN Hua-cheng and GUO Rong-wei.High enthalpy wind tunnel tests of hypersonic inlets with rectangular section[J].Journal of Aerospace Power,2010,25(12):2748-2755.
Authors:YUAN Hua-cheng and GUO Rong-wei
Institution:College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics
Abstract:In this paper, the preliminary test study is conducted on hypersonic inlets with rectangular section at Mach number of 6,5 and 4 in a high enthalpy wind tunnel. The performance and static pressure distributions of the inlet under different back-pressure conditions are obtained. Results indicate that, at design condition(M=6, =0°) , the mass flow capture rate and the 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 that is formed by back-pressure rising can steady in the inner tunnel and the mass flow capture rate is not changed. The mass flow capture rate is not less than 0.77, and the mass-averaged total pressure recovery coefficient is variational 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. The inlet could be started within the range of the Mach number 4.5 and 6.
Keywords:Hypersonic Inlet  Rectangular Section  Wind Tunnel Test
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