连续双扫掠激波/湍流边界层干扰流动特性研究

推进技术 ›› 2019, Vol. 40 ›› Issue (5): 1023-1031.

连续双扫掠激波/湍流边界层干扰流动特性研究

盛发家,谭慧俊,黄河峡,刘亚洲,高婉宁,王卫星

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

发布日期:2021-08-15
作者简介:盛发家，硕士生，研究领域为内流空气动力学。E-mail: sfj636@163.com 通讯作者:谭慧俊，博士，研究领域为内流空气动力学。
基金资助:
国家自然科学基金重点项目(11532007)；国家自然科学基金(11502111)。

Investigation on Flow Characteristics of Successive Bi-Swept Shock Waves/Turbulent Boundary Layer Interaction

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

Published:2021-08-15

摘要/Abstract

摘要： 为了探究连续双扫掠激波/湍流边界层干扰的流动特性，采用仿真方法对一双尖鳍/平板物理模型进行研究。结果表明:双扫掠激波/湍流边界层干扰形成的两个干扰区存在明显的相干现象，虽然第一道扫掠激波/边界层干扰流动仍具有典型的准锥形相似特性，但受其干扰所形成的非均匀流的影响，第二道扫掠激波/边界层干扰却不再具有准锥形相似特性，同时第二个干扰区将影响其上游临近气流的运动甚至影响第一个干扰区的再附线和分离线等结构。两个干扰区形成各自的λ波结构，并且沿着流向两个干扰区内的激波结构相互汇聚，最终合并为单个更强的λ波结构；不仅如此，两个干扰区内还形成了复杂的旋涡结构，包括一级主旋涡和二级主旋涡，这些旋涡向下游运动，最终融合成一个尺度更大的锥形主旋涡。

关键词: 激波；湍流；边界层干扰；流动特性；主旋涡

Abstract: In order to explore the flow characteristics of successive bi-swept shock waves/turbulent boundary layer interaction， numerical simulation is applied to study a double-fins/plate physical model. The results show that the two interaction regions of the bi-swept shocks/boundary layer interaction flow interfere with each other. Though the interaction region formed by the first swept shock maintains its quasi-conical similarity nature， due to the non-uniform flow downstream of the first shock， the quasi-conical similarity nature is no longer applicable to the second swept shock/boundary layer interaction. In addition， the second interaction region will affect the adjacent upstream flow and it even alters the behavior of the reattachment line and separation line induced by the first shock. Two λ-shaped shocks emerge in the two interaction regions， and these shocks converge along streamwise direction， and eventually merge into a stronger single λ-shaped shock. Furthermore， complex vortical structures are generated in the two interaction regions， including the first main vortex， the second main vortex. The two vortices move downstream and coalesce to a larger conical main vortex.

Key words: Shock waves；Turbulent；Boundary layer interaction；Flow characteristics；Main vortex

盛发家,谭慧俊,黄河峡,刘亚洲,高婉宁,王卫星. 连续双扫掠激波/湍流边界层干扰流动特性研究[J]. 推进技术, 2019, 40(5): 1023-1031.

SHENG Fa-jia,TAN Hui-jun,HUANG He-xia,LIU Ya-zhou,GAO Wan-ning,WANG Wei-xing. Investigation on Flow Characteristics of Successive Bi-Swept Shock Waves/Turbulent Boundary Layer Interaction[J]. Journal of Propulsion Technology, 2019, 40(5): 1023-1031.

参考文献

[1] Panaras A G. Review of the Physics of Swept-Shock/Boundary Layer Interactions[J]. Progress in Aerospace Sciences, 1996, 32(2–3): 173-244.
[2] He-xia Huang, Hui-jun Tan, Shu Sun, et al. Evolution of Supersonic Corner Vortex in a Hypersonic Inlet/Isolator Model[J]. Physics of Fluids, 2016, 28(12).
[3] McCabe A. The Three-Dimensional Interaction of a Shock Wave with a Turbulent Boundary Layer[J]. Aeronautical Quarterly, 1966, 17(3): 231-252.
[4] 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.
[5] Korkegi R H. Comparison of Shock-Induced Two and Three Dimensional Incipient Turbulent Seperation[J]. AIAA Journal, 1975, 13(4): 534-535.
[6] Oskam B, Bogdonoff S M, Vas I E. Study of Three-Dimensional Flow Fields Generated by the Interaction of a Skewed Shock Wave with a Turbulent Boundary Layer[R]. AFFDL TR-75-21.
[7] 窦华书, 邓学蓥. 三维激波/湍流边界层干扰产生的起始分离的预测[J]. 空气动力学学报, 1992, 10(1):45-52.
[8] 邓学蓥, 廖锦华. 尖楔和半锥引起的激波/边界层干扰中相关特性研究[J]. 北京航空航天大学学报, 1993, 1(1): 1-5.
[9] 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.
[10] Alvi F S, Settles G S. Structure of Swept Shock Wave/Boundary-Layer Interactions Using Conical Shadowgraphy[C]. Washington DC: 21st Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1990.
[11] Knight D D, Badekast D, Horstmant C C, et al. Quasiconical Flowfield Structure of the Three-Dimensional Single Fin Interaction[J]. AIAA Journal, 1992, 30(12): 2809-2816.
[12] Rodi P E, Dolling D S. Behavior of Pressure and Heat Transfer in Sharp Fin-Induced Turbulent Interactions[J]. AIAA Journal, 1995, 33(11): 2013-2019.
[13] 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, 2016, 55(22): 1-12.
[14] Token K H. Heat Transfer Due to Shock Wave/Turbulent Boundary Layer Interactions on High Speed Weapon Systems[R]. AFFDL TR-74-77.
[15] Kubota H, Stollery J. An Experimental Study of the Interaction Between a Glancing Shock Wave and a Turbulent Boundary Layer[J]. Journal of Fluid Mechanics, 1982, 116(1): 431-458.
[16] Dolling D S, Bogdonoff S M. Upstream Influence in Sharp Fin-Induced Shock Wave Turbulent Boundary-Layer Interaction[J]. AIAA Journal, 1983, 21(1): 143-145.
[17] Zheltovodov A A. Regimes and Properties of Three-Dimensional Separation Flows Initiated by Skewed Compression Shocks[J]. Journal of Applied Mechanics and Technical Physics, 1982, 23(3): 413-418.
[18] Degrez G, Ginoux J. Surface Phenomena in a Three-Dimensional Skewed Shock Wave/Laminar Boundary-Layer Interaction[J]. AIAA Journal, 1984, 22(12): 1764-1769.
[19] 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.
[20] Dolling D S. Upstream Influence in Conically Symmetric Flow[J]. AIAA Journal, 1985, 23(6): 967-969.
[21] Settles G S, Lu F K. Conical Similarity of Shock/Boundary-Layer Interactions Generated by Swept and Unswept Fins[J]. AIAA Journal, 1985, 23(7): 1021-1027.
[22] Knight D D, Horstman C, Bogdonoff S, et al. Structure of Supersonic Turbulent Flow Past a Sharp Fin[J]. AIAA Journal, 1987, 25(10): 1331-1337.
[23] Hsu J C, Settles G S. Holographic Flowfield Density Measurements in Swept Shock Wave/Boundary-Layer Interactions[C]. Washington DC: 30th Aerospace Sciences Meeting and Exhibit, 1992.
[24] Knight D D, Badekast D, Horstmant C C, et al. Quasiconical Flowfield Structure of the Three-Dimensional Single Fin Interaction[J]. AIAA Journal, 1992, 30(12): 2809-2816.
[25] 王宇, 王世芬. 马赫数对后掠激波和湍流边界层干扰特性的影响[J]. 空气动力学学报, 1994, 12(3):313-319.
[26] 邓学蓥, 廖锦华. 锥形干扰中的起始分离研究[J]. 空气动力学学报, 1997, 15(1): 87-93.
[27] 王世芬, 王宇, 刘鹏. 高超音速后掠激波与边界层干扰流场特性[J]. 航空学报, 1993, 14(9): 449-454.
[28] Garrison T J, Settles G S. Flowfield Visualization of Crossing Shock-Wave/Boundary-Layer Interactions[C].Washington DC: 30th Aerospace Sciences Meeting and Exhibit, 1992.
[29] Garrison T J, Settles G S, Narayanswami N, et al. Structure of Crossing-Shock-Wave/Turbulent-Boundary-Layer Interactions[J]. AIAA Journal, 1993, 31(31): 2204-2211.
[30] Hui-jun Tan, Shu Sun, He-xia Huang. Behavior of Shock Trains in a Hypersonic Inlet/Isolator Model with Complex Background Waves[J]. Experiments in Fluids, 2012, 53(6): 1647-1661.
[31] Reinartz B U, Herrmann C D, Ballmann J, et al. Aerodynamic Performance Analysis of a Hypersonic Inlet Isolator Using Computation and Experiment[J]. Journal of Propulsion and Power, 2003, 19(5): 868-875.
[32] Schmitz D, Bissinger N. Design and Testing of 2-D Fixed-Geometry Hypersonic Intakes[C]. Washington DC: 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 1998.　　　　　　　　　　　　　　收稿日期:2018-05-31；修订日期:2018-07-27。基金项目:国家自然科学基金重点项目(11532007)；国家自然科学基金(11502111)。作者简介:盛发家,硕士生,研究领域为内流空气动力学。E-mail: sfj636@163.com通讯作者:谭慧俊,博士,研究领域为内流空气动力学。E-mail: tanhuijun@nuaa.edu.cn(编辑:史亚红)