壁面马赫数分布规律可控的新型内收缩基准流场设计方法

推进技术 ›› 2013, Vol. 34 ›› Issue (4): 433-438.

• 气动热力学 • 下一篇

壁面马赫数分布规律可控的新型内收缩基准流场设计方法

朱伟,张堃元,南向军

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:朱伟(1988—),男,硕士生,研究领域为冲压发动机内流气体动力学。E-mail:zwwder@163.com

Investigation on Basic Flowfield with Controlled Mach Number Gradient for Hypersonic Inward Turning Inlets

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

Published:2021-08-15

摘要/Abstract

摘要： 根据有旋特征线理论,设计出了沿程马赫数下降规律可控的轴对称基准流场,分析了基准流场的几何参数(前缘压缩角及中心体半径)的影响规律,发现选取较小的前缘压缩角和中心体半径有利于得到性能优良的基准流场；然后在设计状态Ma=6时研究了三种典型的马赫数下降规律对这种轴对称流场性能的影响。最后考虑了粘性的影响,并进行了粘性修正探索,结果表明,采用附面层位移厚度修正方法后,基准流场的壁面压力分布和无粘情况吻合良好。 

关键词: 高超内收缩进气道;基准流场;数值模拟;等马赫数梯度 

Abstract: Basic flowfields are vital for streamline traced hypersonic inward turning inlets.With the method of characteristics (MOC) and wall Mach number distribution to study basic flowfield of hypersonic inlet,the effects of basic flowfield geometry parameter and three typical wall Mach number distribution on basic flowfield were studied at Ma=6. The results indicate that the basic flowfield with small leading edge deflection angle and center body radius could have better performances. Finally,visous correction was studied considering the influence of viscous, using the method of boundary layer displacement thickness, the viscous performance parameters of design state are closer to the inviscid design parameters. 

Key words: Hypersonic inward turning inlets；Basic flowfield；Numerical simulation；Constant Mach number gradient

朱伟,张堃元,南向军. 壁面马赫数分布规律可控的新型内收缩基准流场设计方法[J]. 推进技术, 2013, 34(4): 433-438.

ZHU Wei, ZHANG Kun-yuan, NAN Xiang-jun. Investigation on Basic Flowfield with Controlled Mach Number Gradient for Hypersonic Inward Turning Inlets[J]. Journal of Propulsion Technology, 2013, 34(4): 433-438.

参考文献

[1] Mlder S, Szpiro J.Busemman Inlet for Hypersonic Speeds[J].Journal of Spacecraft and Rockets, 1966,3(8):1303-1304.
[2] Billig F S.SCRAM-A Supersonic Combustion Ramjet Missile [R].AIAA 93-2329.
[3] 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,2007,2(3).
[4] Lance S Jacobsen, Chung-Jen Tam, Robert Behdadnia.Starting and Operation of a Streamline-Traced Busemann Inlet at Mach 4[R].AIAA 2006-4508.
[5] Smart M K.Design of Three-Dimensional Hypersonic Inlets with Rectangular to Elliptical Shape Transition[R].AIAA 98-0960.
[6] Smart M K.Experimental Testing of a Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition[ R].AIAA 99-0085.
[7] MatthewsA J,Jones T V.Design and Test of a Modular Waverider Hypersonic Intake[R].AIAA 2005-3379.
[8] Lance S J, Tam Chung-Jen, Robert B.Starting and Operation of a Streamline-Traced Busemann Inlet at Mach 4[R].AIAA 2006-4508.
[9] Taylor T M,David VanWie.Performance Analysis of Hypersonic Shape-Changing Inlets Derived from Morphing Streamline Traced Flowpaths[R].AIAA 2008-2635.
[10] Yabin Xiao, Lianjie Yue, Peng Gong,et al.Investigation on a Truncated Streamline-Traced Hypersonic Busemann Inlet[R].AIAA 2008-2634.
[11] Travis W D, Ioannis Nompelis,Graham V C.Hypersonic Inward Turning Inlets:Design and Optimization[R].AIAA 2006-297.
[12] Yancheng You, Dewang Liang.Cross Section Controllable Hypersonic Inlet Design Using Streamline Tracing and Osculating Axisymmetric Concepts[R].AIAA 2007-5379.
[13] Yancheng You, Dewang Liang.Cross Section Controllable Hypersonic Inlet Design Using Streamline Tracing and Osculating Axisymmetric Concepts[R].AIAA 2007-5379.
[14] Cebeci T, Bradshaw P.Physical and Computational Aspects of Convective HeatTransfer [M].New York:Sping-Verlag, 1994

壁面马赫数分布规律可控的新型内收缩基准流场设计方法

Investigation on Basic Flowfield with Controlled Mach Number Gradient for Hypersonic Inward Turning Inlets

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