类水滴进口高超声速内收缩进气道设计及数值研究

李永洲; 张堃元; 南向军; 张林

类水滴进口高超声速内收缩进气道设计及数值研究

南京航空航天大学能源与动力学院,南京 210016

基金项目: 国家自然科学基金(90916029)

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出版历程
- 收稿日期: 2011-06-25
- 刊出日期: 2012-06-28

Design and numerical investigation of hypersonic inward turning inlet with water-drop like shape intake

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

摘要

摘要: 采用压升规律可控的轴对称基准流场,结合流线追踪及截面渐变等技术设计了类水滴进口转圆形出口高超内收缩进气道构型,在设计点和接力点进行了数值模拟,并和设计参数相同的矩形转圆形内收缩进气道进行了比较.结果表明:设计点和接力点两者总体性能相当,类水滴进口进气道出口流场较均匀,并且具有更好的起动性能.此外,类水滴进口的几何非对称性造成了进气道整个流场结构的非对称.
- 高超声速进气道 /
- 内收缩进气道 /
- 方转圆 /
- 类水滴进口 /
- 数值仿真
Abstract: The water-drop like shape to circular shape transition hypersonic inward turning inlet has been designed with the technology of streamline tracing and gradual change section,using an axisymmetric basic flowfield with controllable pressure rising distribution.Numerical simulations were conducted on both design point and translation point,and the comparison of performance was performed with the rectangular to circular shape transition inward turning inlet with the same design parameters.The results indicate that two types of inward turning inlet have the roughly equivalent general performance,while the water-drop like shape intake has a more uniform exit flowfield and a better starting characteristic.Furthermore,the flowfiled structure of water-drop like shape intake is asymmetric due to the asymmetric geometry shapes.
- hypersonic inlet /
- inward turning inlet /
- rectangular to circular shape transition /
- water-drop like shape intake /
- numerical simulation

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参考文献(18)

[1]	Voland R T,Auslende A H,Smart M K.CIAM/NASA Mach 6.5 scramjet flight and ground test .AIAA 1999-4848,1999.
[2]	Trexler C A.Performance of an inlet for an integrated scramjet concept[J].Aircraft,1974,11(9):589-591.
[3]	Molder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
[4]	Van Wie D M,Molder S.Applications of Busemann inlet designs for flight at hypersonic speeds .AIAA 1992-1210,1992.
[5]	Billig F S.SCRAM-A supersonic combustion ramjet missile .AIAA 1993-2329,1993.
[6]	孙波,张堃元,金志光.流线追踪Busemann 进气道马赫数3.85实验研究[J].航空动力学报,2007,22(3):396-399. SUN Bo,ZHANG Kunyuan,JIN Zhiguang.Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet[J].Journal of Aerospace Power,2007,22(3):396-399.(in Chinese)
[7]	Bulman M J,Siebenhaar A.The rebirth of round hypersonic propulsion .AIAA 2006-5035,2006.
[8]	Walker S H,Rodgers F C,Esposita A L.Hypersonic collaborative Australia/United States experiment (HYCAUSE) .AIAA 2005-3254,2005.
[9]	Elvin J D.Integrated inward turning inlets and nozzles for hypersonic air vehicles:US,20070187550A1.3 .2007-08-16.
[10]	Walker S H,Rodgers F.Falcon hypersonic technology overview .AIAA 2005-3253,2005.
[11]	Billig F S,Jacobsen L S.Comparison of planar and axisymmetric flowpaths for hydrogen fueled space access vehicle .AIAA 2003-4407,2003.
[12]	Smart M K.Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition[J].Journal of Propulsion and Power,1999,15(3):408-416.
[13]	Sabean J,Lewis M J.Optimization of a hypersonic inlet with a rectangular to circular transition .AIAA 1999-0612,1996.
[14]	Dissel A F,Kothari A P.Investigation of two-stage-to-orbit air breathing launch-vehicle configurtions[J].Spacecraft Rockets,2006,43(3):568-574.
[15]	NAN Xiangjun,ZHANG Kunyuan.Numerical and experimental investigation on hypersonic inward turning inlets with basic flow field using arc tangent curve law of pressure rise .AIAA 2011-2270,2011.
[16]	南向军,张堃元,金志光,等.压升规律可控的高超声速内收缩进气道设计[J].航空动力学报,2011,26(3):518-523. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Investigation on hypersonic inward turning inlets with controlled pressure gradient[J].Journal of Aerospace Power,2011,26(3):518-523.(in Chinese)
[17]	南向军,张堃元,金志光,等.矩形转圆形高超声速内收缩进气道数值及实验研究[J].航空学报,2011,32(6):988-996. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Numerical and experimental investigation of hypersonic inward turning inlets with rectangular to circular shape transition[J].Acta Aeronautica et Astronautica Sinica,2011,32(6):988-996.(in Chinese)
[18]	Bagaveyev N T,Engbom W A,Bhagwandin V A.Parametric investigation of racetrack-to-circular cross section transition of a dual-mode ramjet isolator .AIAA 2010-0942,2010.