[1]SEDDON J, GOLDSMITH E L.Intake aerodynamics (Second Edition) [M]. Reston: AIAA Education Series, 1999.
[2]BILLIG F S, BAURLE R A, TAM C, et al.Design and analysis of streamline traced hypersonic inlets: AIAA 1999-4974[R]. Reston, VA: AIAA, 1999.
[3]ZUO F Y, M?LDER S.Hypersonic wavecatcher intakes and variable-geometry turbine based combined cycle engines[J].Progress in Aerospace Sciences, 2019, 106:108-144
[4]HUANG H X, TAN H J, LI B F, et al.A review of the shock-dominated flow in a hypersonic inlet/isolator[J].Progress in Aerospace Sciences, 2023, 143:100952-
[5]MA Y, GUO M M, TIAN Y, et al.Recent advances and prospects in hypersonic inlet design and intelligent optimization[J].Aerospace Science and Technology, 2024, 146:108953-
[6]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
[7]SABEAN J W, LEWIS M J.Computational optimization of a hypersonic rectangular-to-circular inlet[J].Journal of Propulsion and Power, 2001, 17(3):571-578
[8]TAYLOR T, VANWEI D.Performance analysis of hypersonic shape-changing inlets derived from morphing streamline traced flowpaths: AIAA-2008-2635[R]. Reston: AIAA, 2008.
[9]尤延铖, 梁德旺, 郭荣伟, 等.高超声速三维内收缩式进气道乘波前体一体化设计研究评述[J].力学进展, 2009, 39(5):513-525
[10]郑晓刚, 施崇广, 张加乐, 等.高超声速三维内转进气道研究进展综述[J].航空学报, 2025, 46(8):60-98
[11]王卫星, 郭荣伟.圆形出口内转式进气道流动特征[J].航空学报, 2016, 37(02):533-544
[12]QIAO W Y, YU A Y, GAO W, et al.Design method with controllable velocity direction at throat for inward-turning inlets[J].Chinese Journal of Aeronautics, 2019, 32(06):1403-1415
[13]王卫星, 朱婷, 张仁涛, 等.高超声速内转式进气道型面流场重构[J].航空学报, 2020, 41(3):183-192
[14]王晓峰, 屈峰, 付俊杰, 等.基于离散伴随的高超内转式进气道气动优化设计[J].航空学报, 2023, 44(19):56-72
[15]XIAO Y B, YUE L J, CHEN L H, et al.Iso-contraction-ratio methodology for the design of hypersonic inward turning inlets with shape transition: AIAA 2012-5978[R]. Reston, VA: AIAA, 2012.
[16]WANG Z A, XIN X A, CHEN R Y, et al.Development and evolution mechanism of streamwise vortex in an inward-turning inlet[J].Journal of Aerospace Engineering, 2023, 237(15):3413-3434
[17]GOLLAN R J, FERLEMANN P G.Parametric geometry, structured grid generation, and initial design study for REST-class hypersonic inlets[C]// Proceedings of the JANNAF Airbreathing Propulsion Subcommittee Meeting. Columbia: JHU CADRE, 2009: 1-26.
[18]BARTH J E, WHEATLEY V, SMART M K, et al.Flow physics inside a shape-transitioning scramjet engine: AIAA 2012-5888[R]. Reston, VA: AIAA, 2012.
[19]BARTH J E, WHEATLEY V, SMART M K.Effects of hydrogen fuel injection in a Mach 12 scramjet inlet[J].AIAA Journal, 2015, 53(10):2907-2919
[20]李永洲, 张堃元, 张留欢.抽吸对高超声速内收缩进气道涡流区及起动性能的影响[J].航空动力学报, 2016, 31(7):1630-1637
[21]ZUO F Y, HUANG G P.Numerical investigation of bleeding control method on section-controllable wavecatcher intakes[J].Acta Astronautica, 2018, 151:572-584
[22]LIU C Q, GAO Y S, TIAN S L, et al.Rortex—A new vortex vector definition and vorticity tensor and vector decompositions[J].Physics of Fluids, 2018, 30(3):035103-
[23]LIU C Q, GAO Y S.Third generation of vortex identification methods: Omega and LiutexRortex based systems[J].Journal of Hydrodynamics, 2019, 31(2):205-223
[24]SMART M K.Experimental testing of a hypersonic inlet with rectangular-to-elliptical shape transition[J].Journal of Propulsion and Power, 2001, 17(2):276-283
[25]YOU Y C, LIANG D W, GUO R W.High enthalpy wind tunnel tests of three-dimensional section controllable internal waverider hypersonic inlet: AIAA-2009-0031[R]. Reston: AIAA, 2009.
[26]李永洲, 张堃元, 孙迪.马赫数可控的方转圆高超声速内收缩进气道试验研究[J].航空学报, 2016, 37(10):2970-2979
[27]李一鸣, 李祝飞, 杨基明, 等.典型高超声速内转式进气道激光散射流场显示[J].航空学报, 2017, 38(12):138-149
[28]LI Y M, LI Z F, YANG J M.Tomography-like flow visualization of a hypersonic inward-turning inlet[J].Chinese Journal of Aeronautics, 2021, 34(1):44-49
[29]DICRISTINA G, KANG K, SONG S J, et al.Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique[J].Journal of Visualization, 2019, 22:359-369
[30]KATO N, LEE G S, LIM J, et al.Flow visualization in a streamline-traced supersonic inlet: AIAA 2024-0111[R]. Reston, VA: AIAA, 2024.
[31]LI Z F, GAO W Z, JIANG H L, et al.Unsteady behaviors of a hypersonic inlet caused by throttling in shock tunnel[J].AIAA Journal, 2013, 51(10):2485-2492
[32]MA Y K, LI Z F, YANG J M.Planar laser scattering visualization of streamwise vortex pairs in a Mach 6 flow[J].Chinese Journal of Aeronautics, 2023, 36(1):166-177
[33]洪雨婷, 闫波, 黄琪, 等.斜激波入射内凹半圆柱面湍流边界层数值模拟[J].推进技术, 2023, 44(4):85-95
[34]KARL S, STEELANT J.Crossflow phenomena in streamline-traced hypersonic intakes[J].Journal of Propulsion & Power, 2018, 34(2):449-459
[35]ZHOU Y Y, ZHAO Y L, WANG L C, et al.Evolution characteristics of streamwise vortex of crossing shock waveturbulent boundary layer interaction[J].Physics of Fluids, 2023, 35(1):016107-
[36]欧吉辉, 万兵兵, 刘建新, 等.高超声速绕钝体熵层基本流特性研究[J].空气动力学学报, 2018, 36(2):238-246
[37]SMITS A J, DUSSAUGE J P.Turbulent shear layers in supersonic flow[M]. New York: Springer Science & Business Media, 2006.