A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows
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摘要
Along with the survey on experimental investigations drawing attention to the drag and heat reduction mechanism, the authors simultaneously focus on the recent advances of numerical simulations on the schemes applied to supersonic/hypersonic vehicles. The CFD study has evolved as an irreplaceable method in scheme evaluation and aircraft optimization. Similar to our previous experimental survey, the advances in drag and heat reduction schemes are reviewed by similar kinds of mechanism in this article, namely the forward-facing cavity, the opposing jet, the aerospike, the energy deposition and their combinational configurations. This review article puts an emphatic eye on the flow conditions, numerical methods, novel schemes and analytical conclusions given in the simulations. Further, the multi-objective design optimization concept has also been illustrated due to the observable advantages of using CFD over experimental method, especially those performances conducted in drag reduction and thermal protection practice, and this would possess reference value in the design of aircraft system.
Along with the survey on experimental investigations drawing attention to the drag and heat reduction mechanism, the authors simultaneously focus on the recent advances of numerical simulations on the schemes applied to supersonic/hypersonic vehicles. The CFD study has evolved as an irreplaceable method in scheme evaluation and aircraft optimization. Similar to our previous experimental survey, the advances in drag and heat reduction schemes are reviewed by similar kinds of mechanism in this article, namely the forward-facing cavity, the opposing jet, the aerospike, the energy deposition and their combinational configurations. This review article puts an emphatic eye on the flow conditions, numerical methods, novel schemes and analytical conclusions given in the simulations. Further, the multi-objective design optimization concept has also been illustrated due to the observable advantages of using CFD over experimental method, especially those performances conducted in drag reduction and thermal protection practice, and this would possess reference value in the design of aircraft system.
Along with the survey on experimental investigations drawing attention to the drag and heat reduction mechanism, the authors simultaneously focus on the recent advances of numerical simulations on the schemes applied to supersonic/hypersonic vehicles. The CFD study has evolved as an irreplaceable method in scheme evaluation and aircraft optimization. Similar to our previous experimental survey, the advances in drag and heat reduction schemes are reviewed by similar kinds of mechanism in this article, namely the forward-facing cavity, the opposing jet, the aerospike, the energy deposition and their combinational configurations. This review article puts an emphatic eye on the flow conditions, numerical methods, novel schemes and analytical conclusions given in the simulations. Further, the multi-objective design optimization concept has also been illustrated due to the observable advantages of using CFD over experimental method, especially those performances conducted in drag reduction and thermal protection practice, and this would possess reference value in the design of aircraft system.
引文
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2.Liang H, Wang YQ, Mb Tong, Zhang JH. Multi-scale strength analysis of bolted connections used in integral thermal protection system. Chin J Aeronaut 2018;31(8):1728–40.
3.Wang ZG, Sun XW, Huang W, Li SB, Yan L. Experimental investigation on drag and heat?ux reduction in supersonic/hypersonic?ows:a survey. Acta Astronaut 2016;129:95–110.
4.Zhang TT, Huang W, Wang ZG, Yan L. A study of airfoil parameterization, modeling and optimization based on the computational?uid dynamics method. J Zhejiang Univ-Sci A(Appl Phys Eng)2016;17(8):632–45.
5.Hayashi K, Aso S, Tani Y. Experimental study on thermal protection system by opposing jet in supersonic?ow. J Spacecraft Rockets 2006;43(1):233–6.
6.Khurana S, Suzuki K, Rathakrishnan E. Effect of vortex-size around spike root and body base on possible hypersonic drag reduction. The 7th international colloquium on bluff body aerodynamics and applications, 2012.
7.Saravanan S, Jagadeesh G, Reddy KPJ. Investigation of missileshaped body with forward-facing cavity at Mach 8. J Spacecraft Rockets 2009;46(3):577–91.
8.Lu HB, Liu WQ. Numerical simulation in in?uence of forwardfacing cavity on aerodynamic heating of hypersonic vehicle.Procedia Eng 2012;29:4096–100.
9.Lu HB. Research on complicated?ow?eld and heat transfer characteristic of forward-facing cavity combined with opposing jet forti?ed thermal protection con?guration[dissertation]. Changsha:National University of Defense Technology;2012[Chinese].
10.Lu HB, Liu WQ. Investigation on thermal protection ef?ciency of hypersonic vehicle nose with forward-facing cavity. J Astronaut 2012;33(8):1013–8[Chinese].
11.Lu HB, Tian SY. Forward-facing cavity:an ef?cient thermal preotection scheme for hyperosnic vehicles. Winded Missile J2015;6:11–5[Chinese].
12.Yuceil B, Dolling DS. A preliminary investigation of the Helmholtz resonator concept for heat?ux reduction. AIAA28 th thermophysics conference. Reston:AIAA; 1993.
13.Engblom WA, Yuceil B, Goldstein D, Dolling D. Hypersonic forward-facing cavity?ow-An experimental and numerical study.33 rd aerospace sciences meeting and exhibit, 1995.
14.Hartmann J, Troll B. On a new method for the generation of sound waves. Phys Rev 1922;20(6):719–27.
15.Engblom WA, Goldstein DB, Ladoon D, Schneider SP. Fluid dynamics of hypersonic forward-facing cavity?ow. J Spacecraft Rockets 1997;34(4):437–44.
16.Silton SI, Goldstein DB. Ablation onset in unsteady hypersonic?ow about nose tip with cavity. J Thermophys Heat Transfer2000;14(3):421–34.
17.Silton SI, Goldstein DB. Use of an axial nose-tip cavity for delaying ablation onset in hypersonic?ow. J Fluid Mech2005;528:297–321.
18.Huang W, Zhao ZT, Yan L, Zhou Y, Zhang RR. Parametric study on the drag and heat?ux reduction mechanism of forwardfacing cavity on a blunt body in supersonic?ows. Aerosp Sci Technol 2017;71:619–26.
19.Yadav R, Guven U. Aerothermodynamics of a hypersonic vehicle with a forward-facing parabolic cavity at nose. Proc Inst Mech Eng Part G-J Aerosp Eng 2014;228(10):1863–74.
20.Yadav R, Guven U. Aerodynamic heating of a hypersonic projectile with forward-facing ellipsoid cavity at Nose. J Spacecraft Rockets 2015;52(1):157–65.
21.Seiler F, Srulijes J, Gimenez PM, Mangold P. Heat?uxes inside a cavity placed at the nose of a projectile measured in a shock tunnel at Mach 4.5New results in numerical and experimental?uid mechanics VI. Berlin Heidelberg:Springer; 2008. p. 309–16.
22.Bazyma L, Kuleshov V. Numerical and experimental investigation of cylinder cavity?ows. Proc Inst Mech Eng, Part G:J Aerosp Eng 2007;221(2):253–8.
23.Sun XW, Guo ZY, Huang W, Li SB, Yan L. Drag and heat reduction mechanism induced by a combinational novel cavity and counter?owing jet concept in hypersonic?ows. Acta Astronaut 2016;126:109–19.
24.Huang W. A survey of drag and heat reduction in supersonic?ows by a counter?owing jet and its combinations. J Zhejiang Univ-Sci A(Appl Phys Eng)2015;16(7):551–61.
25.Huang W, Yan L. Progress in research on mixing techniques for transverse injection?ow?elds in supersonic cross?ows. J Zhejiang Univ-Sci A(Appl Phys Eng)2013;14(8):554–64.
26.Huang W, Yan L. Transverse jet in supersonic cross?ows. Aerosp Sci Technol 2016;50:183–95.
27.Hayashi K, Aso S. Effect of pressure ratio on aerodynamic heating reduction due to opposing jet. 33rd?uid dynamics conference and exhibit, 2003.
28.Huang W, Jiang YP, Yan L, Liu J. Heat?ux reduction mechanism induced by a combinational opposing jet and cavity concept in supersonic?ows. Acta Astronaut 2016;121:164–71.
29.Huang W, Yan L, Liu J, Jin L, Tan JG. Drag and heat reduction mechanism in the combinational opposing jet and acoustic cavity concept for hypersonic vehicles. Aerosp Sci Technol2015;42:407–14.
30.Rong YS, Sun J, Liu WQ, Zhan RJ. Heat?ux reduction research in hypersonic?ow with opposing jet. Proceedings of world academy of science, engineering and technology, 2012.
31.Rong YS. Research on the thermal protection by opposing jet and transpiration for vehicle leading edge and the complex?ow alogrithm[dissertation]. Changsha:National University of Defense Technology; 2012[Chinese].
32.Rong YS. Drag reduction research in supersonic?ow with opposing jet. Acta Astronaut 2013;91:1–7.
33.Rong YS, Wei YC, Zhan RJ. Research on thermal protection by opposing jet and transpiration for high speed vehicle. Aerosp Sci Technol 2016;48:322–7.
34.Lu HB, Liu WQ. Numerical investigation on properties of attack angle for an opposing jet thermal protection system. Chin Phys B2012;21(8):289–94.
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