高超声速进气道/隔离段内流特性研究进展

推进技术 ›› 2018, Vol. 39 ›› Issue (10): 2252-2273.

高超声速进气道/隔离段内流特性研究进展

黄河峡¹,谭慧俊¹,庄逸¹,盛发家¹,孙姝²

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学民航/飞行学院，江苏南京 210016

发布日期:2021-08-15
作者简介:黄河峡，男，博士，讲师，研究领域为飞行器进气道技术、内流空气动力学等。E-mail: huanghexia@nuaa.edu.cn 通讯作者:谭慧俊，男，博士，教授，研究领域为飞行器进气道技术、可压缩流体力学与流动控制方法等。
基金资助:
国家自然科学基金(11532007；11772156；11172136)；新世纪优秀人才支持计划(NCET-11-0831)；江苏省高校

Progress in Internal Flow Characteristics of Hypersonic Inlet/Isolator

Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Jiangsu Province Key Laboratory of Aerospace Power System，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Civil Aviation，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 作为超燃冲压发动机的增压部件，高超声速进气道/隔离段内部存在一系列的复杂流动现象，本文概述了该领域的相关研究进展。高超声速进气道/隔离段内存在多种激波/边界层干扰现象，并受到膨胀波系等的干扰，使其特性偏离了传统基于简化模型的研究结果，具有显著的三维干扰特征、多波组合干扰特征，并在通道内诱导出了显著的二次流，特别是角区旋涡流动。隔离段内存在复杂的激波和膨胀波结构，这些背景波系在隔离段内不断反射，形成显著的流向和横向参数间断。当出口流道发生几何或热力壅塞时，隔离段内会出现更为复杂的激波串现象。激波串和上游背景波系、角涡相干，呈现出明显的偏向性，并在前移过程中可能会出现两种特殊的动态前移过程。尽管最近对高超声速进气道/隔离段内流特性的认识得到了极大地提高，但仍然有较多的基础问题亟待解决。

关键词: 高超声速进气道/隔离段；激波/边界层干扰；背景波系；角区旋涡；激波串

Abstract: Inlet and isolator are the compression components of scramjet engines， the internal flows of which are fairly complicated. The latest research achievements focused on the internal flow of inlet/isolator are reviewed. Firstly， there are complex shock/boundary layer interactions in the inlet/isolator， and the interactions are affected by the expansion waves. The characteristics of the shock/boundary interactions depart from the canonical theories based on simplified model. The interactions behave quite three-dimensional and involve multiple shock waves/ boundary layers interaction， besides， the complex interactions will induce significant secondary flow， especially the corner vortex flow. Then， there are complex shock-expansion systems in the isolator， which reflect in the isolator leading to significant streamwise and transverse parameter discontinuities. In addition， when the exit flow path is mechanical or thermal choked， a more complicated flow phenomenon， named shock train， will appear. The shock train interacts with the upstream background waves as well as the corner vortex， and behaves directionality. When the shock train propagates upstream， two typical dynamic transitions may occur. Although the related knowledge of the internal flow characteristics of hypersonic inlet/isolator has been improved greatly， there still remain some basic problems to be uncovered in the future.

Key words: Hypersonic inlet/isolator；Shock wave/boundary layer interaction；Background waves；Corner vortex；Shock train

黄河峡,谭慧俊,庄逸,盛发家,孙姝. 高超声速进气道/隔离段内流特性研究进展[J]. 推进技术, 2018, 39(10): 2252-2273.

HUANG He-xia¹,TAN Hui-jun¹,ZHUANG Yi¹,SHENG Fa-jia¹,SUN Shu². Progress in Internal Flow Characteristics of Hypersonic Inlet/Isolator[J]. Journal of Propulsion Technology, 2018, 39(10): 2252-2273.

参考文献

[1] Mahoney J J. Inlets for Supersonic Missiles [M]. New York: AIAA Education Series, 1991.
[2] Segal C. The Scramjet Engine: Processes and Characteristics[M]. Cambridge: Cambridge University Press, 2009.
[3] Curran E T, Heiser W H, Pratt D T, et al. Fluid Phenomena in Scramjet Combustion Systems[J]. Annual Review of Fluid Mechanics, 1996, 28(1): 323-360.
[4] 吴颖川, 贺元元, 余安远, 等. 展向截断曲面乘波压缩进气道气动布局[J]. 航空动力学报, 2013, 28(7):1570-1575.
[5] 李永洲, 张堃元. 基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计[J]. 航空学报, 2015, 36(1): 289-301.
[6] 南向军, 张堃元, 金志光. 采用新型基准流场的高超内收缩进气道试验研究[J]. 航空学报, 2014, 35(1):90-96.
[7] Zhang K Y. Research Progress of Hypersonic Inlet Inverse Design Based on Curved Shock Compression System[R]. AIAA 2015-3647.
[8] Curran E T, Murthy S N B. Scramjet Propulsion[M]. New York: American Institute of Aeronautics and Astronautics, 2000.
[9] Matsuo K, Miyazato Y, Kim H D. Shock Train and Pseudo-Shock Phenomena in Internal Gas Flows[J]. Progress in Aerospace Sciences, 1999, 35(1): 33-100.
[10] Holger B and John K H. Shock Wave Boundary Layer Interactions[M]. Cambridge: Cambridge University press, 2011.
[11] Délery J M. Shock Wave/Turbulent Boundary Layer Interaction and Its Control[J]. Progress in Aerospace Sciences, 1985, 22(4): 209-280.
[12] Gaitonde D V. Progress in Shock Wave/Boundary Layer Interactions[J]. Progress in Aerospace Sciences, 2015, 72: 80-99.
[13] Simeonides G, Haase W, Manna M. Experimental, Analytical, and Computational Methods Applied to Hypersonic Compression Ramp Flows[J]. AIAA Journal, 1994, 32(2): 301-310.
[14] Krishnan L, Sandham N D, Steelant J. Shock-Wave/Boundary-Layer Interactions in a Model Scramjet Intake [J]. AIAA Journal, 2009, 47(7): 1680-1691.
[15] Chung K M, Lu F K. Hypersonic Turbulent Expansion-Corner Flow with Shock Impingement[J]. Journal of Propulsion and Power, 1995, 11(3): 441-447.
[16] White M E, Ault D A. Expansion Corner Effects on Hypersonic Shock Wave/Turbulent Boundary-Layer Interactions[J]. Journal of Propulsion and Power, 1996, 12(6): 1169-1173.
[17] Zhang Y, Tan H, Zhuang Y, et al. Influence of Expansion Waves on Cowl Shock/Boundary Layer Interaction in Hypersonic Inlets[J]. Journal of Propulsion and Power, 2014, 30(5): 1183-1191.
[18] Zhufei Li and Jiming Yang. Leading Edge Bluntness Effects on Shock Wave Boundary Layer Interactions near a Convex Corner[R]. AIAA 2015-3601.
[19] Sathianarayanan A, Verma S. Experimental Investigation of a Mach 4 Shock-Wave Turbulent Boundary Layer Interaction near an Expansion Corner[R]. AIAA 2015-0112.
[20] 张晓嘉, 梁德旺, 黄国平. 二元高超声速进气道内压缩通道/隔离段曲面构型[J]. 推进技术, 2008, 29(1):49-53. (ZHANG Xiao-jia, LIANG De-wang, HUANG Guo-ping. Curved Surface of Internal Contraction Tunnel/Isolator of Two Dimensional Hypersonic Inlet[J]. Journal of Propulsion Technology, 2008, 29(1): 49-53.)
[21] Panaras A G. Review of the Physics of Swept-Shock/Boundary Layer Interactions[J]. Progress in Aerospace Sciences, 1996, 32(2): 173-244.
[22] Korkegi R H. A Simple Correlation for Incipient-Turbulent Boundary-Layer Separation Due to a Skewed Shock Wave [J]. AIAA Journal, 1973, 11(11): 1578-1579.
[23] Oskam B. Three-Dimensional Flow Fields Generated by the Interaction of a Swept Shock Wave with a Turbulent Boundary Layer[D]. Princeton: Princeton University, 1975.
[24] Kubota H, Stollery J L. An Experimental Study of the Interaction Between a Glancing Shock Wave and a Turbulent Boundary Layer[J]. Journal of Fluid Mechanics, 1982, 116: 431-458.
[25] Alvi F S, Settles G S. Physical Model of the Swept Shock Wave/Boundary-Layer Interaction Flowfield[J]. AIAA Journal, 1992, 30(9): 2252-2258.
[26] Dolling D S, McClure W B. Flowfield Scaling in Sharp Fin-Induced Shock Wave/Turbulent Boundary-Layer Interaction[J]. AIAA Journal, 1985, 23(2): 201-206.
[27] Dolling D S. Upstream Influence in Conically Symmetric Flow[J]. AIAA Journal, 1985, 23(6): 967-969.
[28] Koide S, Saida N, Ogata R. Correlation of Separation Angles Induced by Glancing Interactions[J]. AIAA Journal, 1996, 34(10): 2198-2200.
[29] Panaras A G. Numerical Investigation of the High-speed Conical Flow Past a Sharp Fin[J]. Journal of Fluid Mechanics, 1992, 236: 607-633.
[30] Knight D D, Badekast D, Horstmant C C, et al. Quasi-conical Flowfield Structure of the Three-Dimensional Single Fin Interaction[J]. AIAA Journal, 1992, 30(12): 2809-2816.
[31] Rodi P E, Dolling D S. Behavior of Pressure and Heat Transfer in Sharp Fin-Induced Turbulent Interactions[J]. AIAA Journal, 2015, 33(11): 2013-2019.
[32] Fang J, Yao Y, Zheltovodov A A, et al. Investigation of Three-Dimensional Shock Wave/Turbulent-Boundary-Layer Interaction Initiated by a Single Fin[J]. AIAA Journal, 2017, 55(22): 509-523.
[33] Dolling D S. Fifty Years of Shock-Wave/Boundary-Layer Interaction Research: What Next?[J]. AIAA Journal, 2001, 39(8): 1517-1531.
[34] Reda D C, Murphy J D. Shock Wave/Turbulent Boundary-Layer Interactions in Rectangular Channels[J]. AIAA Journal, 1973, 11(2): 139-140.
[35] Dussauge J P, Piponniau S. Shock /Boundary-Layer Interactions: Possible Sources of Unsteadiness[J]. Journal of Fluids & Structures, 2008, 24(8): 1166-1175.
[36] Haddad C, Ardissone J P, Debieve J F. Space and Time Organization of a Shock Wave/Turbulent Boundary Layer Interaction[J]. Aerospace Science and Technology, 2005, 9(7): 561-572.
[37] Bookey P, Wyckham C, Smits A. Experimental Investigations of Mach 3 Shock Wave Turbulent Boundary Layer Interactions[R]. AIAA 2005-4899.
[38] Burton D M F, Titchener N A, Babinsky H. Corner Effect and Separation in Transonic Channel Flows[J]. Journal of Fluid Mechanics, 2011, 679: 247-262.
[39] Burton D M F, Babinsky H D M F. Corner Separation Effects for Normal Shock Wave/Turbulent Boundary Layer Interactions in Rectangular Channels[J]. Journal of Fluid Mechanics, 2012, 707(3): 287-306.
[40] Babinsky H, Oorebeek J, Cottingham T G. Corner Effects in Reflecting Oblique Shock-Wave/Boundary Layer Interactions[R]. AIAA 2013-0859.
[41] Benek J A, Suchyta C J, Babinsky H. The Effect of Wind Tunnel Size and Shock Strength on Incident Shock Boundary Layer Interaction Experiments[R]. AIAA 2014-3336.
[42] Benek J A, Suchyta C J, Babinsky H. The Effect of Wind Tunnel Size on Incident Shock Boundary Layer Interaction Experiments [R]. AIAA 2013-0862.
[43] Helmer D B, Campo L M, Eaton J K. Three-Dimensional Features of a Mach 2.1 Shock/Boundary Layer Interaction[J]. Experiments in Fluids, 2012, 53(5):1347-1368.
[44] Ethan E W, Driscoll J F. Shock Wave Boundary Layer Interactions in Rectangular Inlets: Three-Dimensional Separation Topology and Critical Points[J]. Journal of Fluid Mechanics, 2014, 756: 328-353.
[45] Wang B, Sandham N D, Hu Z, et al. Numerical Study of Oblique Shock Wave/Boundary Layer Interaction Considering Sidewall Effects[J]. Journal of Fluid Mechanics, 2015, 767: 526-561.
[46] Funderburk M, Narayanaswamy V. Experimental Investigation of Primary and Corner Shock Boundary Layer Interactions at Mild Back Pressure Ratios[J]. Physics of Fluids, 2016, 28(8).
[47] Desikan S L N, Job Kurian. Mixing Studies in Supersonic Flow Employing Strut Based Hypermixers[R]. AIAA 2005-3643.
[48] Chung J T, Kuo C L. Numerical Investigations on Simple Variable Geometry for Improving Scramjet Isolator Performance[R]. AIAA 2006-4509.
[49] Tan H J, Sun S, Huang H X. Behavior of Shock Trains in a Hypersonic Inlet/Isolator Model with Complex Background Waves[J]. Experiments in Fluids, 2012, 53(6):1647-1661.
[50] Huang H, Sun S, Tan H, et al. Characterization of Two Typical Unthrottled Flows in Hypersonic Inlet/Isolator Models[J]. Journal of Aircraft, 2015, 52(5): 1715-1721.
[51] Herrmann C, Koschel W. Experimental Investigation of the Internal Compression Inside a Hypersonic Intake[R]. AIAA 2002-4130.
[52] H?berle J, Gülhan A. Investigation of Two-Dimensional Scramjet Inlet Flowfield at Mach 7[J]. Journal of Propulsion and Power, 2008, 24(3): 446-459.
[53] Tan H J, Sun S, Yin Z L. Oscillatory Flows of Rectangular Hypersonic Inlet Unstart Caused by Downstream Mass-Flow Choking[J]. Journal of Propulsion and Power, 2012, 25(1): 138-147.
[54] Li Z, Gao W, Jiang H, et al. Unsteady Behaviors of a Hypersonic Inlet Caused by Throttling in Shock Tunnel [J]. AIAA Journal, 2013, 51(10): 2485-2492.
[55] Ben-Dor G. Shock Wave Reflection Phenomena[M]. Berlin Heidelberg: Springer, 2007.
[56] 杨旸, 姜宗林, 胡宗民. 激波反射现象的研究进展[J]. 力学进展, 2012, 42(2): 141-161.
[57] 杨基明, 李祝飞, 朱雨建, 等. 激波的传播与干扰[J]. 力学进展, 2016, 46(1): 541-587.
[58] Li H, Ben-dor G. A Parametric Study of Mach Reflection in Steady Flows[J]. Journal of Fluid Mechanics, 1997, 341: 101-125.
[59] Hiller R. Shock-Wave/Expansion-Wave Interactions and the Transition Between Regular and Mach Reflection [J]. Journal of Fluid Mechanics, 2007, 575(9): 399-424.
[60] Matheis J, Hickel S. On the Transition between Regular and Irregular Shock Patterns of Shock-Wave/Boundary-Layer Interactions[J]. Journal of Fluid Mechanics, 2015, 776(4): 200-234.
[61] Mahapatra D, Jagadeesh G. Studies on Unsteady Shock Interactions near a Generic Scramjet Inlet[J]. AIAA Journal, 1971, 47(9): 2223-2231.
[62] Jiao X, Chang J, Wang Z, et al. Mechanism Study on Local Unstart of Hypersonic Inlet at High Mach Number [J]. AIAA Journal, 2015, 53(10): 1-11.
[63] 尤延铖, 梁德旺, 黄国平. 内乘波式进气道内收缩基本流场研究[J]. 空气动力学学报, 2008, 26(2): 203-207.
[64] 王娇, 黄河峡, 谭慧俊. 捕获型线对内转式进气道外压段几何与气动特性的影响[J]. 航空动力学报, 2017, 32(4): 890-899.
[65] Huang H X, Tan H J, Sun S, et al, Evolution of Supersonic Corner Vortex in a Hypersonic Inlet/Isolator Model[J]. Physics of Fluids, 2016, 28(12).
[66] Reddy D R, Weir L J. Three-Dimensional Viscous Analysis of a Mach 5 Inlet and Comparison with Experimental Data[J]. Journal of Propulsion and Power, 2015, 8(2): 432-440.
[67] Karl S Steelant. Crossflow Phenomena in Streamline-Traced Hypersonic Intakes[J]. Journal of Propulsion and Power, 2017, (1).
[68] 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试验研究[J]. 航空学报, 2011, 32(6): 988-996.
[69] Marconi F. Internal Corner Flow Fields [R]. AIAA 79-0014.
[70] 张涵信. 分离流与旋涡运动的结构分析[M]. 北京:国防工业出版社, 2002.
[71] Kalkhoran I M, Smart M K. Supersonic Vortex Breakdown during Vortex/Cylinder Interaction[J]. Journal of Fluid Mechanics, 1998, 369(2): 351-380.
[72] Kalkhoran I M, Smart M K. Aspects of Shock Wave-Induced Vortex Breakdown[J]. Progress in Aerospace Sciences, 2000, 36(1): 63-95.
[73] Neumann E P, Lustwerk F. Supersonic Diffusers for Wind Tunnels[J]. Journal of Applied Mechanics, 1949, 16(2): 195-202.
[74] Yamauchi H, Choi B, Kouchi T, et al. Mechanism of Mixing Enhanced by Pseudo-Shock Wave[R]. AIAA 2009-0025.
[75] Gnani F, Zare-Behtash H, Kontis K. Pseudo-Shock Waves and Their Interactions in High-Speed Intakes [J]. Progress in Aerospace Sciences, 2016, 82: 36-56.
[76] Yi Shi-He, Chen Zhi. Review of Recent Experimental Studies of the Shock Train Flow Field in the Isolator [J].Acta Physica Sinica, 2015, 64(19).
[77] Raj N O P, Venkatasubbaiah K. A New Approach for the Design of Hypersonic Scramjet Inlets[J]. Physics of Fluids, 2012, 24 (8).
[78] Kumar A, Singh D J, Trexler C A. Numerical Study of the Effects of Reverse Sweep on Scramjet Inlet Performance[J]. Journal of Propulsion and Power, 1992, 8(3): 714-719.
[79] 王成鹏. 非对称来流条件下超燃冲压发动机隔离段气动特性研究[D]. 南京:南京航空航天大学, 2005.
[80] 曹学斌. 矩形隔离段流动特性及控制规律研究[D]. 南京:南京航空航天大学, 2011.
[81] 王成鹏, 张堃元, 金志光, 等. 非均匀超声来流矩形隔离段内流场实验[J]. 推进技术, 2004, 25(4): 349-353. (WANG Cheng-peng, ZHANG Kun-yuan, JIN Zhi-guang, et al. Experimental Investigation on Internal Flow in Rectangular Isolator under Non-Uniform Supersonic Flow[J]. Journal of Propulsion Technology, 2004, 25(4): 349-353.)
[82] 张堃元, 王成鹏, 杨建军, 等. 带高超进气道的隔离段流动特性[J]. 推进技术, 2002, 23(4): 311-314. (ZHANG Kun-yuan, WANG Cheng-peng, YANG Jian-jun, et al. Investigation of Flow in Isolator of Hypersonic Inlet[J]. Journal of Propulsion Technology, 2002, 23(4): 311-314.)
[83] Wang C P, Zhang K Y, Yang J J. Analysis of Flows in Scramjet Isolator Combined with Hypersonic Inlet[R]. AIAA 2005-24.
[84] Sajben M, Bogar T J, Kroutil J C. Experimental Study of Flows in a Two-Dimensional Inlet Model [J]. Journal of Propulsion and Power, 1985, 1(2): 109-117.
[85] Wagner J, Yuceil K, Clemens N. Velocimetry Measurements of Unstart of an Inlet-Isolator Model in Mach 5 Flow [J]. AIAA Journal, 2010, 48(9): 1875-1888.
[86] 张航, 谭慧俊, 孙姝. 进口斜激波、膨胀波干扰下等直隔离段内的激波串特性[J]. 航空学报, 2010, 31(9): 1733-1739.
[87] Papamoschou D, Johnson A. Unsteady Phenomena in Supersonic Nozzle Flow Separation[R]. AIAA 2006-3360.
[88] Reijasse P, Corbel B, Soulevant D. Unsteadiness and Asymmetry of Shock-In Separation in a Planar Two-Dimensional Nozzle: A Flow Description [R]. AIAA 99-3694.
[89] Johnson A D, Papamoschou D. Instability of Shock-Induced Nozzle Flow Separation[J]. Physics of Fluids, 2010, 22(1).
[90] Papamoschou D, Zill A, Johnson A. Supersonic Flow Separation in Planar Nozzles[J]. Shock Waves, 2009, 19(3): 171-183.
[91] Bourgoing A, Reijasse P. Experimental Analysis of Unsteady Separated Flows in a Supersonic Planar Nozzle [J]. Shock Waves, 2005, 14(4): 251-258.
[92] Su W Y, Zhang K Y. Back-Pressure Effects on the Hypersonic Inlet-Isolator Pseudoshock Motions[J]. Journal of Propulsion and Power, 2013, 29(6): 1391-1399.
[93] 田旭昂, 王成鹏, 程克明. Ma5斜激波串动态特性实验研究[J]. 推进技术, 2014, 35(8): 1030-1039. (TIAN Xu-ang, WANG Cheng-peng, CHENG Ke-ming. Experimental Investigation of Dynamic Characteristics of Oblique Shock Train in Mach 5 Flow[J]. Journal of Propulsion Technology, 2014, 35(8): 1030-1039.)
[94] Fischer C, Olivier H. Experimental Investigation of the Internal Flow Field of a Scramjet Engine [R]. AIAA 2009-7369.
[95] Fischer C, Olivier H. Experimental Investigation of the Shock Train in an Isolator of a Scramjet Inlet[R]. AIAA 2011-2220.
[96] Lin K C, Tam C J. Effects of Temperature and Heat Transfer on Shock Train Structures inside Constant-Area Isolators[R]. AIAA 2006-817.
[97] Frauholz S, Hosters N, Reinartz B U. Fluid-Structure Interaction in the Context of a Scramjet Intake[R]. AIAA 2014-2449.
[98] Ma Fh, Li J, Yang V, et al. Thermo Acoustic Flow Instability in a Scramjet Combustor[R]. AIAA 2005-3824.
[99] 曹学斌, 张堃元. 超燃冲压发动机隔离段非对称来流下激波串受迫振荡流动研究[J]. 空气动力学学报, 2011, 29(2): 135-141.
[100] Bruce P J K. Unsteady Shock Wave Dynamics[J]. Journal of Fluid Mechanics, 2008, 603: 463-473.
[101] Su W Y, Ji Y X, Chen Y. Effects of Dynamic Backpressure on Pseudoshock Oscillations in Scramjet Inlet-Isolator[J]. Journal of Propulsion and Power, 2016, 32(2): 516-528.
[102] Wang C P, Tian X A, Cheng K M, et al. Numerical Analysis of Pseudo-Shock Flow Diffusion Phenomenon in Variable Cross-Section Ducts[J]. Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, 2008, 222(8): 1109-1121.
[103] 王卫星. 非常规隔离段流场特征与气动性能的数值研究[D]. 南京:南京航空航天大学, 2008.
[104] Lin P. Geometric Effects on Precombustion Shock Train in Constant Area Isolators [R]. AIAA 93-1838.
[105] Tan J, Wu J, Wang Z. Experimental and Numerical Investigations on Flow Fields and Performance of Dual Combustion Ramjet[J]. Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, 2013, 228(6): 920-929.
[106] Gnos A V, Watson E C, Seebaugb W R, et al. Investigation of Flow Fields within Large Scale Hypersonic Inlet Models[R]. NASA TN-D7150, 1973.
[107] Tan H J, Sun S. Preliminary Study of Shock Train in a Curved Variable-Section Diffuser[J]. Journal of Propulsion and Power, 2015, 24(2): 245-252.
[108] 谭慧俊, 郭荣伟. 二维弯曲等截面管道中的激波串特性研究[J]. 航空学报, 2006, 27(6): 1039-1045.
[109] Byrne S O’, Doolan M. Analysis of Transient Thermal Choking Processes in a Model Scramjet Engine[J]. Journal of Propulsion and Power, 2000, 16(5): 808-814.
[110] Karl S, Schramm J M, Hannemann K. Transient Fluid-Combustion Phenomena in a Model Scramjet[J]. Journal of Fluid Mechanics, 2013, 722(9): 85-120.
[111] McDaniel K S, Edwards J R. Three-Dimensional Simulation of Thermal Choking in a Model Scramjet Combustor[R]. AIAA 2001-0382.
[112] McDaniel K S, Edwards J R. Simulation of Thermal Choking in a Model Scramjet Combustor[R]. AIAA 99-3411.
[113] Frost M A, Gangurde D Y, Paull A, et al. Boundary-Layer Separation Due to Combustion-Induced Pressure Rise in a Supersonic Flow[J]. AIAA Journal, 2009, 47(4): 1050-1053.
[114] Laurence S J, Schramm J M, Karl S, et al. An Experimental Investigation of Steady and Unsteady Combustion Phenomena in the HyShot II Combustor[R]. AIAA 2011-2310.
[115] Laurence S J, Lieber D, Schramm J M, et al. Incipient Thermal Choking and Stable Shock-Train Formation in the Heat-Release Region of a Scramjet Combustor, Part I: Shock-Tunnel Experiments[J]. Combustion and Flame, 2014, 162(4): 921-931.
[116] Steva T B, Goyne C P, Rockwell Jr R D, et al. Comparison of a Direct-Connect and Freejet Dual-Mode Scramjet[J]. Journal of Propulsion and Power, 2015, 31(5): 1380-1392.
[117] Waltrup P J, Billig F S. Structure of Shock Waves in Cylindrical Ducts[J]. AIAA Journal, 1973, 11(10): 1404-1408.
[118] Sullins G, McLafferty G. Experimental Results of Shock Trains in Rectangular Ducts[R]. AIAA 92-5103.
[119] Oka T, Ono D, Miyazota Y. Study of Shock Trains and Pseudo-Shock Waves in Constant Area Ducts[R]. AIAA 2014-0949.
[120] Fotia M L, Driscoll J F. Isolator-Combustor Interactions in a Direct-Connect Ramjet-Scramjet Experiment [J]. Journal of Propulsion and Power, 2012, 28(1): 83-95.
[121] Fischer C, Olivier H. Experimental Investigation of Wall and Total Temperature Influence on a Shock Train [J]. AIAA Journal, 2014, 52(4): 757-766.
[122] Geerts J S, Yu K H. Shock Train/Boundary-Layer Interaction in Rectangular Isolators[J]. AIAA Journal, 2016, 54(11): 3450-3464.
[123] Klomparens R L, Driscoll J F, Gamb M. Unsteadiness Characteristics and Pressure Distribution of an Oblique Shock Train[R]. AIAA 2015-1519.
[124] Smart M K. Flow Modeling of Pseudoshocks in Backpressured Ducts[J]. AIAA Journal, 2015, 53(12): 3577-3588.
[125] Huang H X, Tan H J, Wang J, et al. A Fluidic Control Method of Shock Train in Hypersonic Inlet/Isolator[R]. AIAA 2014-3846.
[126] Tan H J, Li C H, Zhang Y. Investigation of a Fluidic Shock Control Method for Hypersonic Inlets[J]. Journal of Propulsion and Power, 2010, 26(5): 1072-1083.
[127] Cao X B, Zhang K Y. Experimental Investigation of the Short Isolator with the Ramp under Asymmetric Incoming Flow[R]. AIAA 2010-6554.
[128] Valdivia A, Yuceil K B, Wagner J L, et al. Control of Supersonic Inlet-Isolator Unstart Using Active and Passive Vortex Generators[J]. AIAA Journal, 2014, 52(6): 1207-1218.
[129] Okuni H, Araki H, Park M K, et al. Experimental Study on Oscillation Control of Pseudo-Shock in Channel Divided by Porous Plate[J]. Transactions of the Japan Society of Mechanical Engineers Part B, 2001, 67(655): 704-711.
[130] Weiss A, Olivier H. Behaviour of a Shock Train under the Influence of Boundary-Layer Suction by a Normal Slot[J]. Experiments in Fluids, 2012, 52(2): 273-287.
[131] Narayanaswamy V, Raja L L, Clemens N T. Control of Unsteadiness of a Shock Wave/Turbulent Boundary Layer Interaction by Using a Pulsed-Plasma-Jet Actuator [J]. Physics of Fluids, 2012, 24(7).
[132] Mohd Y Ali, Farrukh S Alvi. Studies on the Control of Shock Wave-Boundary Layer Interaction Using Steady Microactuators [R]. AIAA 2011-3425.
[133] Ogawa H, Babinsky H, P?tzold M, et al. Shock-Wave/Boundary-Layer Interaction Control Using Three-Dimensional Bumps for Transonic Wings[J]. AIAA Journal, 2008, 46(6): 1442-1452.
[134] Zhang Y, Tan H, Tian F C, et al. Control of Incident Shock/Boundary-Layer Interaction by a Two-Dimensional Bump [J]. AIAA Journal, 2014, 52(4): 767-776.
[135] Hafenrichter E S, Lee Y, Dutton J C, et al. Normal Shock/Boundary-Layer Interaction Control Using Aeroelastic Mesoflaps[J]. Journal of Propulsion and Power, 2003, 19(3): 464-472.
[136] Garnier E, Adams N, Sagaut P. Large Eddy Simulation for Compressible Flows[M]. Berlin: Springer, 2013.
[137] Boles J A, Choi J I, Edwards J R, et al. Multi-Wall Recycling/Rescaling Method for Inflow Turbulence Generation [R]. AIAA 2010-1099.
[138] Morgan B, Duraisamy K, Lele S K. Large-Eddy Simulations of a Normal Shock Train in a Constant-Area Isolator [J]. AIAA Journal, 2014, 52(3): 539-558.
[139] Emmert T, Lafon P, Bailly C. Numerical Study of Self-Induced Transonic Flow Oscillations behind a Sudden Duct Enlargement[J]. Physics of Fluids, 2009, 21(10).
[140] Koo H, Raman V. Large-Eddy Simulation of a Supersonic Inlet-Isolator[J]. AIAA Journal, 2012, 50(7): 1596-1613.
[141] Boles J A, Hagenmaier M A, Hsu K Y. Analysis of Hybrid LES/RANS Simulations of a Back-Pressured Supersonic Isolator[R]. AIAA 2011-5825.
[142] Burns R A, Koo H, Raman V, et al. Improved Large-Eddy Simulation Validation Methodology: Application to Supersonic Inlet/Isolator Flow[J]. AIAA Journal, 2015, 53(4): 817-831.
[143] Quaatz J F, Giglmaier M, Hickel S, et al. Large-Eddy Simulation of a Pseudo-Shock System in a Laval Nozzle [J]. International Journal of Heat and Fluid Flow, 2014, 49: 108-115.
[144] Edwards J R. Large-Eddy /Reynolds Averaged Navier-Stokes Simulation of Shock-Train Development in a Coil-Laser Diffuser[R]. Raleigh: North Carolina State University at Raleigh, 2014.
[145] Olson B J, Lele S K. A Mechanism for Unsteady Separation in Over-Expanded Nozzle Flow[J]. Physics of Fluids, 2013, 25(11).
[146] Larsson J, Laurence S, Bermejo-Moreno I, et al. Incipient Thermal Choking and Stable Shock-Train Formation in the Heat-Release Region of a Scramjet Combustor, Part II: Large Eddy Simulations[J]. Combustion and Flame, 2015, 162(4): 907-920.
[147] Zettervall N, Nordinbates K, Fureby C. Understanding Scramjet Combustion Using LES of the HyShot II Combustor [R]. AIAA 2015-3615.
[148] Carroll B F, Dutton J C. Multiple Normal Shock Wave/Turbulent Boundary-Layer Interactions[J]. Journal of Propulsion and Power, 1992, 8(2): 441-448.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2017-09-07；修订日期:2018-02-01。基金项目:国家自然科学基金(11532007；11772156；11172136)；新世纪优秀人才支持计划(NCET-11-0831)；江苏省高校优势学科建设工程资助项目；江苏省普通高校研究生科研创新计划资助项目(KYLX_0303)。作者简介:黄河峡,男,博士,讲师,研究领域为飞行器进气道技术、内流空气动力学等。E-mail: huanghexia@nuaa.edu.cn通讯作者:谭慧俊,男,博士,教授,研究领域为飞行器进气道技术、可压缩流体力学与流动控制方法等。E-mail: thj@263.net