一种用于前缘钝化高超声速进气道设计评估的CFD/特征线组合方法及其应用

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1585-1592.

• 气动热力学与总体技术 • 下一篇

一种用于前缘钝化高超声速进气道设计评估的CFD/特征线组合方法及其应用

高文智¹,李祝飞¹,杨基明¹,谭慧俊²

中国科学技术大学近代力学系激波实验室,安徽合肥 230027;中国科学技术大学近代力学系激波实验室,安徽合肥 230027;中国科学技术大学近代力学系激波实验室,安徽合肥 230027;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:高文智(1990—) ,男,博士生,研究领域为高超声速进气道。E-mail:ensureme@mail.ustc.edu.cn
基金资助:
国家自然科学基金(11132010)。

A Combined CFD/Characteristic Method for Design and Performance Prediciton of Hypersonic Inlet with Leading Edge Bluntness

Department of Modern Mechanics, University of Science and Technology of China,Anhui 230027, China;Department of Modern Mechanics, University of Science and Technology of China,Anhui 230027, China;Department of Modern Mechanics, University of Science and Technology of China,Anhui 230027, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

摘要： 为便于前缘钝化高超声速进气道设计与性能分析,将CFD方法与特征线法相结合,提出一种高超声速钝化锥/楔流场的快速精确计算方法(CCM方法)。该方法将CFD方法的精度与特征线方法的效率相结合,可进行前缘钝化高超声速进气道的快速设计与性能分析。利用CCM方法设计了一种前缘钝化两级锥轴对称进气道构型,分析了前缘钝化对进气道前体波系位置的影响,并采用CFD模拟开展了相应的对比考察和性能参数影响研究。结果表明,对于轴对称进气道,当前缘钝化半径较小时,进气道前体波系位置及流动性能基本不变；当钝化半径增至一定的尺度后,前缘激波向外偏移以及进气道性能参数的下降开始显露并渐趋明显。在设计状态点附近,低来流Ma下前缘钝化对轴对称进气道性能影响更为显著。对于该轴对称进气道构型,前缘钝化半径在10%捕获半径内变化时,进气道流量系数、出口截面总压恢复系数等参数变化幅度均在10%以内；进气道自起动Ma数略有下降。 

关键词: 高超声速;进气道设计;前缘钝化;特征线法 

Abstract: A combined CFD with characteristic method (CCM) was proposed for fast and accurate computation of hypersonic blunt cone/wedge flowfield. Both the accuracy of CFD and the efficiency of characteristic method are well combined in CCM, and it can be used for design and performance analysis of hypersonic inlet with leading edge bluntness. By using CCM, a bi-cone axisymmetric inlet with leading edge bluntness was designed and the effects of leading edge bluntness on its performance were evaluated. Correlated validation and inlet performance research were carried out by using CFD simulation and good agreement was found between CFD and CCM. The results show that the effect of leading edge bluntness on axisymmetric inlet performance is related to blunt scale and freestream condition. As the blunt radius varies within a limited scale, the changes in the behaviors of the inlet flow are negligible, beyond which the decrease in the performance appears and tends to be more severe. As the freestream Mach number decreases, more effects of leading edge bluntness on axisymmetric inlet performance are shown up. It was also found that for the present designed inlet configuration, flow parameters of exit cross section vary within 10% and the self-start Ma decreases a little as the blunt scale increases to 10% cowl radius. 

Key words: Hypersonic; Inlet design; Leading edge bluntness; Method of characteristics

高文智,李祝飞,杨基明,谭慧俊. 一种用于前缘钝化高超声速进气道设计评估的CFD/特征线组合方法及其应用[J]. 推进技术, 2013, 34(12): 1585-1592.

GAO Wen-zhi¹,LI Zhu-fei¹,YANG Ji-ming¹,TAN Hui-jun². A Combined CFD/Characteristic Method for Design and Performance Prediciton of Hypersonic Inlet with Leading Edge Bluntness[J]. Journal of Propulsion Technology, 2013, 34(12): 1585-1592.

参考文献

[1] Curran E T, Murthy S N B.Progress in Astronautics and Aeronautics[M].USA:American Institute of Aeronautics and Astronautics,2001.
[2] Tincher D,Lane J.On the Design of a Hypersonic Waverider Test Bed Vehicle:A First Step to Outer Planet Exploration[R].AIAA 92-2305.
[3] Benson J L,Maslowe S A.Bluntness and Boundary-Layer Displacement Effects on Hypersonic Inlet Flowfields[J].Journal of Spacecraft and Rockets,1966,3(9):1394-1402.
[4] 王金光,张堃元.前缘非对称钝化对高超声速进气道气动性能的影响[C].三亚:第四届高超声速科技学术会议,2011.
[5] Santos W F N.Bluntness Impact on Lift-to-Drag Ratio[J].Journal of Spacecraft and Rockets, 2009,6(2):329-339.
[6] Billig F S.Shock-Wave Shapes around Spherical and Cylindrical-Nosed Bodies[J].Journal of Spacecraft and Rockets,1967,4(6):822-823.
[7] 王晓栋,乐嘉陵.前缘对进气道性能影响的数值模拟[J].推进技术,2002,3(6):460-462.(WANG Xiao-dong, LE Jia-ling.Numerical Simulation of Effects of leading Edge on the Performance of Inlet [J].Journal of Propulsion Technology, 2002,3(6):460-462.)
[8] 王卫星, 郭荣伟.基于边界层转捩的高超声速进气道特性[J].航空学报, 2012,3(10):1772-1780.
[9] 童秉纲,孔详言,邓国华.气体动力学[M].北京:高等教育出版社,1990.
[10] Zucrow M J,Hoffman J D.Gas Dynamics[M].USA:John Wiley & Sons,Inc.,1977.
[11] Anderson B H.Design of Supersonic Inlets by a Computer Program Incorporating the Method of Characteristics[R].NASA TN D-4960,9.
[12] 潘瑾, 张堃元,王磊.几种超声速非常规压缩系统的研究[J].推进技术, 2009,0(6):673-676.(PAN Jin,ZHANG Kun-yuan,WANG Lei.Study of Several Supersonic Non-Conventional Compression Surfaces[J].Journal of Propulsion Technology, 2009,0(6):673-676.)
[13] 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, 2011,6(3):518-523.
[14] 向有志, 张堃元,王磊,等.壁面压升可控的高超轴对称进气道优化设计[J].航空动力学报, 2011,6(10):2193-2199.
[15] 李祝飞,黄舶,杨基明,等.激波风洞中高超声速进气道[C].无锡:第三届高超声速科技学术会议,2010.

一种用于前缘钝化高超声速进气道设计评估的CFD/特征线组合方法及其应用

A Combined CFD/Characteristic Method for Design and Performance Prediciton of Hypersonic Inlet with Leading Edge Bluntness

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