Research on Control of Hypersonic Shock Wave/boundary Layer Interactions by Double Micro-ramps

doi:10.3969/j.issn.1000-1093.2016.09.011

Abstract

Abstract: Shock wave/boundary layer interaction (SWBLI) is a ubiquitous phenomenon encountered in hypersonic flow field, and a flow separation induced by SWBLI leads to the performance degradation of hypersonic inlet. Detached-eddy simulation model and finite volume method are used with adaptive mesh refinement to simulate the flow separation controlled by micro-ramps, which is induced by SWBLIs in hypersonic flow for Ma=7. The control effect of micro-ramps on flow separation is discussed based on flow velocity, pressure gradient, transformed form factor and total pressure loss, and the control mechanism of double micro-ramps is investigated. The research results indicate that the reciprocal induction between streamwise vortex pairs generated by two micro-ramps accelerates the entrainment of vortex pairs generated by each micro-ramp, consequently the effect of two micro-ramps for eliminating the separation bubble is better than that of a single micro-ramp. As the height of micro-ramps decrease, the total pressure loss shows a trend of first decrease and then increase. The effects of streamwise vortex intensity and form resistance are synthetically discussed. The micro-ramps with 35%δ′ in height (separation bubble thickness) have the best effect on controlling the separation bubble, by which the separation bubble is decreased to disappear the reversed flow, and the peak of transformed form factor and the total pressure loss are reduced by about 86% and 1.9%, respectively.

Key words: fluid mechanics, hypersonic flow, shock wave/boundary layer interaction, micro-ramp, flow separation control, streamwise vortex

CLC Number:

O354.4

DONG Xiang-rui， CHEN Yao-hui， DONG Gang， LIU Yi-xin. Research on Control of Hypersonic Shock Wave/boundary Layer Interactions by Double Micro-ramps[J]. Acta Armamentarii, 2016, 37(9): 1624-1632.

References

［1］ Ferri A, Guidonia A D. Experimental results with airfoils tested in the high speed tunnel at Guidonia, NACA-TM-946[R]. Washington, DC, US: National Advisory Committee for Aeronautics, 1940.
[2] Mallinson S G, Gai S L, Mudford N R. The interaction of a shock wave with a laminar boundary layer at a compressing corner in high-enthalpy flows including real gas effects[J]. Journal of Fluid Mechanics, 1997, 342:1-35.
[3] MacComack R W. Numerical solution of the interaction of a shock wave with a laminar boundary layer[J]. Lecture Notes in Physics, 1971, 8:151-163.
[4] Urbin G, Knight D D, Zheltovodov A A. Large eddy simulation of a supersonic compression corner. I[C]∥38th Aerospace Sciences Meeting and Exhibit. Reno, NV, US: AIAA, 2000.
[5] Garnier E, Sagaut P, Deville M. Large eddy simulation of shock/boundary layer interaction[J]. AIAA Journal, 2002, 40(10): 1935-1944.
[6] Knight D, Yan H, Panaras A G, et al. Advances in CFD prediction of shock wave turbulent boundary layer interactions[J]. Progress in Aerospace Sciences, 2003, 39(2):121-184.
[7] Donovan J F. Control of shock wave/turbulent boundary layer interactions using tangential injection[C]∥34th Aerospace Sciences Meeting and Exhibit. Reno, NV, US: AIAA, 1996.
[8] Gefroh D, Loth E, Dutton C, et al. Aeroelastically deflecting flaps for shock/boundary layer interaction control[J]. Journal of Fluids and Structures, 2003, 17(7):1001-1016.
[9] Caraballo E, Webb N, Little J, et al. Supersonic inlet flow control using plasma actuators[C]∥47th Aerospace Sciences Meeting. Orlando, FL, US: AIAA, 2009.
[10] Babinsky H, Ogawa H. SBLI control for wings and inlets[J]. Shock Waves, 2008, 18(2):89-96.
[11] Anderson B H, Tinapple J, Surber L. Optimal control of shock wave turbulent boundary layer interactions using micro-array actuation[C]∥3rd AIAA Flow Control Conference. San Francisco, CA, US: AIAA, 2006.
[12] Lee S, Loth E, Wang C. LES of supersonic turbulent boundary layers with μVG's[C]∥25th AIAA Applied Aerodynamics Conference. Miami, FL, US: AIAA, 2007.
[13] Sharma P, Ghosh S. A novel vortex generator for mitigation of shock-induced separation[C]∥52nd Aerospace Sciences Meeting. National Harbor, MD, US: AIAA, 2014.
[14] Zhang B, Zhao Q, Xiang X, et al. An improved micro-vortex generator in supersonic flows[J]. Aerospace Science and Technology, 2015, 47: 210-215.
[15] Verma S, Chidambaranathan M. Transition control of Mach to regular reflection induced interaction using an array of micro ramp vane-type vortex generators[J]. Physics of Fluids, 2015, 27(10): 107102.
[16] Yan Y, Chen C, Lu P, et al. Study on shock wave-vortex ring interaction by the micro vortex generator controlled ramp flow with turbulent inflow [J]. Aerospace Science and Technology, 2013, 30(1): 226-231.
[17] Yan Y, Liu C. Study on the ring-like vortical structure in MVG controlled supersonic ramp flow with different inflow conditions[J]. Aerospace Science and Technology, 2014, 35(1):106-115.
[18] 闫文辉, 吴小虹, 徐晶磊,等. 高马赫数下激波湍流边界层干扰数值研究[J]. 航空计算技术，2011, 41(5):56-60.
YAN Wen-hui, WU Xiao-hong, XU Jing-lei, et al. Numerical study of shock-wave turbulent boundary layer interaction at high Mach number[J]. Aeronautical Computing Technique, 2011, 41(5): 56-60.(in Chinese)
[19] 薛大文, 陈志华, 孙晓晖，等. 微型三角楔超声速绕流特性的研究[J]. 工程力学, 2013, 30(4): 455-460.
XUE Da-wen, CHEN Zhi-hua, SUN Xiao-hui, et al. Investigations on the flow characteristics of supersonic flow past a micro-ramp[J]. Engineering Mechanics, 2013, 30(4):455-460. (in Chinese)
[20] 薛大文, 陈志华, 孙晓晖，等. 翼型绕流分离的微楔控制[J]. 工程力学, 2014, 31(8): 217-222.
XUE Da-wen, CHEN Zhi-hua, SUN Xiao-hui, et al. Micro-ramp control of the boundary separation induced by the flow past an airfoil [J]. Engineering Mechanics, 2014, 31(8): 217-222. (in Chinese)
[21] 刘刚, 刘伟, 牟斌,等. 涡流发生器数值计算方法研究[J]. 空气动力学学报, 2007, 25(2): 241-244.
LIU Gang, LIU Wei, MU Bin, et al. CFD numerical simulation investigation of vortex generators [J]. Acta Aerodynamica Sinica, 2007, 25(2): 241-244. (in Chinese)
[22] Menter F R. Zonal two equation k-ω turbulence models for aerodynamic flow [C]∥24th Fluid Dynamics Conference. Orlando, FL, US: AIAA, 1993.
[23] 刘学强, 伍贻兆, 程克明,等. 用基于M-SST湍流模型的DES方法数值模拟喷流流场[J]. 力学学报, 2004, 36(4): 401-406.
LIU Xue-qiang, WU Yi-zhao, CHENG Ke-ming, et al. Computation of lateral turbulent jets using M-SST DES Model[J]. Acta Mechanica Sinica, 2004, 36(4):401-406. (in Chinese)
[24] Ozawa T, Lesbros S, Hong G. LES of synthetic jets in boundary layer with laminar separation caused by adverse pressure gradient[J]. Computers & Fluids, 2010, 39(5): 845-858.
[25] Canepa E, Lengani D, Satta F, et al. Boundary layer separation control on a flat plate with adverse pressure gradients using vortex generators[C]∥ASME Turbo Expo 2006: Power for Land, Sea, and Air. Barcelona, Spain: American Society of Mechanical Engineers, 2006: 1211-1220.

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