矩形转圆形高超声速内收缩进气道数值及试验研究

doi:CNKI:11-1929/V.20110217.1420.000

流体力学与飞行力学

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矩形转圆形高超声速内收缩进气道数值及试验研究

南向军¹, 张堃元¹, 金志光¹, 孙波²

1. 南京航空航天大学能源与动力学院, 江苏南京 210016;
2. 南京理工大学机械工程学院, 江苏南京 210094

收稿日期:2010-09-08 修回日期:2010-12-14 出版日期:2011-06-25 发布日期:2011-06-24
通讯作者: Tel.: 025-84892201-2100 E-mail: zkype@nuaa.edu.cn E-mail:zkype@nuaa.edu.cn
作者简介:南向军(1985- ) 男,博士研究生。主要研究方向:内流气体动力学。 E-mail: nanxj12@163.com张堃元(1943- ) 男,硕士,教授,博士生导师。主要研究方向:内流气体动力学。 Tel: 025-84892201-2100 E-mail: zkype@nuaa.edu.cn 金志光(1977- ) 男,博士,副教授,硕士生导师。主要研究方向:内流气体动力学。 E-mail: j_zg77@yahoo.com.cn孙波(1980- ) 男,博士,讲师,硕士生导师。主要研究方向:内流气体动力学。 E-mail: hypersun@mail.njust.edu.cn
基金资助:
国家自然科学基金 (90916029)

Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition

NAN Xiangjun¹, ZHANG Kunyuan¹, JIN Zhiguang¹, SUN Bo²

1. College of Energy & Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China

Received:2010-09-08 Revised:2010-12-14 Online:2011-06-25 Published:2011-06-24

摘要/Abstract

摘要： 采用压力梯度先增大后减小压升规律轴对称基准流场,结合流线追踪及截面渐变技术设计了矩形转圆形内收缩进气道模型,并采用4°斜楔模拟飞行器前体,对前体、进气道一体化模型进行了数值模拟和风洞试验,初步得到了该进气道的流场结构及总体性能。设计点和接力点的数值模拟结果表明该进气道可在马赫数Ma=4~6状态下正常工作,且具有良好的总体性能。在设计点Ma=6、正4°攻角状态进行的风洞试验表明,该进气道增压比为41.2,总压恢复达0.45,至少可抵抗200倍来流静压的反压。

关键词: 高超声速进气道, 基准流场, 压升规律, 数值模拟, 风洞试验

Abstract: With pressure gradient on the wall of the inlet’s basic flow field increasing at the front part then decreasing at the rear part, using streamline tracing and varying section techologies, a hypersonic inward turning inlet with rectangular to circular shape transition integrated into 4° wedge forebody, is designed and investigated with numerical simulation and experimental method. The flow field structure and performance of the inlet are primarily obtained. The simulation results of design points and take-over speeds indicate that this inlet can operate normally over the Mach number range of 4-6 and has good performance with 4° angle of attack. The inlet model is tested in a hypersonic wind tunnel at Mach number 6 with 4° angle of attack. And the experimental results indicate that the scaled inlet model’s total pressure recovery is 0.45. It can generate a compression ratio of 41.2 and withstand a back pressure ratio of 200 relative to tunnel static pressure.

Key words: hypersonic inlets, basic flowfield, law of pressure rise, numerical analysis, wind tunnel test

中图分类号:

V231

南向军, 张堃元, 金志光, 孙波. 矩形转圆形高超声速内收缩进气道数值及试验研究[J]. 航空学报, 2011, 32(6): 988-996.

NAN Xiangjun, ZHANG Kunyuan, JIN Zhiguang, SUN Bo. Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(6): 988-996.

参考文献

[1] Busemann A. Die achsensymmetrische kegeligelleber schallstromung[J]. Luftfahrtforschung, 1942(19):137-144.

[2] Mlder S, Szpiro J. Busemman inlet for hypersonic speeds[J]. Journal of Spacecraft and Rockets, 1966, 3(8): 1303-1304.

[3] Billig F S, Johns H U, Laurel M. SCRAM—a supersonic combustion ramjet missile . AIAA-1993-2329, 1993.

[4] Billig F S, Baurle R A, Tam C J, et al. Design and analysis of streamline traced hypersonic inlets. AIAA-1999-4974, 1999.

[5] 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)

[6] Sun B, Zhang K Y, Wang C P, et al. Investigation on a streamtraced hypersonic Busemann inlet[J]. Journal of Aerospace Engineering, 2009, 224(1): 57-63.

[7] Matthews A J, Jones T V. Design and test of a modular waverider hypersonic intake. AIAA-2005-3379, 2005.

[8] Barkmeyer D, Starkey R P, Lewis M J. Inverse waverider design for inward turning inlets. AIAA-2005-3915, 2005.

[9] Smart M K. Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition. AIAA-1998-960, 1998.

[10] You Y C, Liang D W. Cross section controllable hypersonic inlet design using streamline tracing and osculating axisymmetric concepts. AIAA-2007-5379, 2007.

[11] You Y C, Liang D W, Guo R W. High enthalpy wind tunnel tests of three-dimensional section controllable internal waverider hypersonic inlet. AIAA-2009-31, 2009.

[12] Taylor T M,VanWie D. Performance analysis of hypersonic shape—changing inlets derived from morphing streamline traced flowpaths. AIAA-2008-2635, 2008.

[13] Jacobsen L S, Tam C J, Behdadnia R. Starting and operation of a streamline-traced Busemann inlet at Mach 4. AIAA-2006-4508, 2006.

[14] Xiao Y B, Yue L J, Gong P, et al. Investigation on a truncated streamline-traced hypersonic Busemann inlet. AIAA-2008-2634, 2008.

[15] Drayna T W, Nompelis I, Candler G V. Hypersonic inward turning inlets: design and optimization. AIAA-2006-297, 2006.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

矩形转圆形高超声速内收缩进气道数值及试验研究

Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition

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