Abstract: drag reduction and thermal protection is very important for hypersonic vehicles, and a counterflowing jet and its combinations is one of the most promising drag and heat release reduction strategies. In the current survey, research progress on the drag and heat release reduction induced by a counterflowing jet and its combinations is summarized. Three combinatorial configurations are considered, namely the combination of the counterflowing jet and a forward-facing cavity, the combination of the counterflowing jet and an aerospike, and the combination of the counterflowing jet and energy deposition. In conclusion, some recommendations are provided, especially for jet instability protection, for the tradeoff between drag and heat release reductions, and for the critical points for the operational and geometric parameters in the flow mode transition.

逆向喷流及其组合体在超声速气流中减阻防热功效研究进展

[1]Ahmed, M.Y.M., Qin, N., 2010. Metamodels for aerothermodynamic design optimization of hypersonic spiked blunt bodies. Aerospace Science and Technology, 14(5):364-376.

[2]Ahmed, M.Y.M., Qin, N., 2011. Recent advances in the aerothermodynamics of spiked hypersonic vehicles. Progress in Aerospace Sciences, 47(6):425-449.

[3]Ahmed, M.Y.M., Qin, N., 2012. Surrogate-based multi-objective aerothermodynamic design optimization of hypersonic spiked bodies. AIAA Journal, 50(4):797-810.

[4]Aruna, S., Anjalidevi, S.P., 2012. Computational study on the influence of jet on reduction of drag over cone flare bodies in hypersonic turbulent flow. Procedia Engineering, 38:3635-3648.

[5]Bushnell, D.M., 2004. Shock wave drag reduction. Annual Review of Fluid Mechanics, 36(1):81-96.

[6]Chen, L.W., Wang, G.L., Lu, X.Y., 2011. Numerical investigation of a jet from a blunt body opposing a supersonic flow. Journal of Fluid Mechanics, 684:85-110.

[7]Daso, E.O., Beaulieu, W., Hager, J.O., 2002. Prediction of drag reduction in supersonic and hypersonic flows with counter-flow jets. AIAA Paper 2002-5115.

[8]Daso, E.O., Pritchett, V.E., Wang, T.S., et al., 2009. Dynamics of shock dispersion and interactions in supersonic freestreams with counterflowing jets. AIAA Journal, 47(6):1313-1326.

[9]Engblom, W.A., Goldstein, D.B., Ladoon, D., et al., 1997. Fluid dynamics of hypersonic forward-facing cavity flow. Journal of Spacecraft and Rockets, 33(3):353-359.

[10]Feszty, D., Badcock, K.J., Richards, B.E., 2004. Driving mechanisms of high-speed unsteady spiked body flows, Part 1: pulsation mode. AIAA Journal, 42(1):95-106.

[11]Finley, P.J., 1966. The flow of a jet from a body opposing a supersonic free stream. Journal of Fluid Mechanics, 26:337-368.

[12]Fomin, V.M., Maslov, A.A., Malmuth, N.D., et al., 2002. Influence of a counterflow plasma jet on supersonic blunt-body pressures. AIAA Journal, 40(6):1170-1177.

[13]Ganiev, Y.C., Gordeev, V.P., Krasilnikov, A.V., et al., 2000. Aerodynamic drag reduction by plasma and hot-gas injection. Journal of Thermophysics and Heat Transfer, 14(1):10-17.

[14]Geng, Y.F., Yan, C., 2010. Numerical investigation on drag and heat-transfer reduction using combined spike and forward facing jet method. Acta Aerodynamica Sinica, 28(4):436-440 (in Chinese).

[15]Geng, Y.F., Yu, J., Kong, W.X., 2012. Investigation on a new method of adaptive drag reduction and non-ablation thermal protection system for hypersonic vehicles. Acta Aerodynamica Sinica, 30(4):492-501 (in Chinese).

[16]Gerdroodbary, M.B., Hosseinalipour, S.M., 2010. Numerical simulation of hypersonic flow over highly blunted cones with spike. Acta Astronautica, 67(1-2):180-193.

[17]Gerdroodbary, M.B., Bishehsari, S., Hosseinalipour, S.M., et al., 2012. Transient analysis of counterflowing jet over highly blunt cone in hypersonic flow. Acta Astronautica, 73:38-48.

[18]Gerdroodbary, M.B., Imani, M., Ganji, D.D., 2014. Heat reduction using counterflowing jet for a nose cone with aerodisk in hypersonic flow. Aerospace Science and Technology, 39:652-665.

[19]Gnemmi, P., Srulijes, J., Roussel, K., et al., 2003. Flowfield around spike-tipped bodies for high attack angles at Mach 4.5. Journal of Spacecraft and Rockets, 40(5):622-631.

[20]Hayashi, K., Aso, S., Tani, Y., 2006. Experimental study on thermal protection system by opposing jet in supersonic flow. Journal of Spacecraft and Rockets, 43(1):233-235.

[21]He, K., Chen, J.Q., Dong, W.Z., 2006. Penetration mode and drag reduction research in hypersonic flows using a counter-flow jet. Chinese Journal of Theoretical and Applied Mechanics, 38(4):438-445 (in Chinese).

[22]Ho, S.Y., Paull, A., 2006. Coupled thermal, structural and vibrational analysis of a hypersonic engine for flight test. Aerospace Science and Technology, 10(5):420-426.

[23]Huang, W., 2014. Design exploration of three-dimensional transverse jet in a supersonic crossflow based on data mining and multi-objective design optimization approaches. International Journal of Hydrogen Energy, 39: 3914-3925.

[24]Huang, W., Wang, Z.G., 2009. Numerical study of attack angle characteristics for integrated hypersonic vehicle. Applied Mathematics and Mechanics (English Edition), 30(6):779-786.

[25]Huang, W., Yan, L., 2013. Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 14(8):554-564.

[26]Huang, W., Luo, S.B., Liu, J., et al., 2010. Effect of cavity flame holder configuration on combustion flow field performance of integrated hypersonic vehicle. Science China Technological Sciences, 53(10):2725-2733.

[27]Huang, W., Wang, Z.G., Jin, L., et al., 2011. Effect of cavity location on combustion flow field of integrated hypersonic vehicle in near space. Journal of Visualization, 14(4):339-351.

[28]Huang, W., Pourkashanian, M., Ma, L., et al., 2012a. Effect of geometric parameters on the drag of the cavity flameholder based on the variance analysis method. Aerospace Science and Technology, 21(1):24-30.

[29]Huang, W., Li, S.B., Liu, J., et al., 2012b. Investigation on high angle of attack characteristics of hypersonic space vehicle. Science China Technological Sciences, 55(5):1437-1442.

[30]Huang, W., Wang, Z.G., Ingham, D.B., et al., 2013a. Design exploration for a single expansion ramp nozzle (SERN) using data mining. Acta Astronautica, 83:10-17.

[31]Huang, W., Liu, J., Yan, L., et al., 2013b. Multiobjective design optimization of the performance for the cavity flameholder in supersonic flows. Aerospace Science and Technology, 30(1):246-254.

[32]Huang, W., Liu, J., Jin, L., et al., 2014a. Molecular weight and injector configuration effects on the transverse injection flow field properties in supersonic flows. Aerospace Science and Technology, 32(1):94-102.

[33]Huang, W., Yang, J., Yan, L., 2014b. Multi-objective design optimization of the transverse gaseous jet in supersonic flows. Acta Astronautica, 93:13-22.

[34]Huang, W., Yan, L., Liu, J., et al., 2015. Drag and heat reduction mechanism in the combinational opposing jet and acoustic cavity concept for hypersonic vehicles. Aerospace Science and Technology, 42:407-414.

[35]Huebner, L.D., Utreja, L.J., 1993. Mach 10 bow shock behavior of forward facing nose cavity. Journal of Spacecraft and Rockets, 30(3):291-297.

[36]Jiang, Z.L., Liu, Y.F., Han, G.L., et al., 2009. Experimental demonstration of a new concept of drag reduction and thermal protection for hypersonic vehicles. Acta Mechanica Sinica, 25(3):417-419.

[37]Karagozian, A.R., 2010. Transverse jets and their control. Progress in Energy and Combustion Science, 36(5):531-553.

[38]Khamooshi, A., Taylor, T., Riggins, D.W., 2007. Drag and heat transfer reductions in high-speed flows. AIAA Journal, 45(10):2401-2413.

[39]Knight, D., 2008. Survey of aerodynamic drag reduction at high speed by energy deposition. Journal of Propulsion and Power, 24(6):1153-1167.

[40]Kulkarni, V., Reddy, K.P.J., 2008. Enhancement in counterflow drag reduction by supersonic jet in high enthalpy flows. Physics of Fluids, 20:016103.

[41]Ladoon, D.W., Schneider, S.P., Schmisseur, J.D., 1998. Physics of resonance in a supersonic forward-facing cavity. Journal of Spacecraft and Rockets, 35(5):626-632.

[42]Lawrence, D., Anthony, M., Ellis, J., 1995. Experimental results on the feasibility of an aerospike for hypersonic missiles. AIAA Paper 95-0737.

[43]Li, H.Y., Eri, Q.T., 2007. Numerical simulation of aerodynamic heating reduction due to opposing jet in supersonic flow. Proceedings of the Fifth International Conference on Fluid Mechanics, Shanghai, China.

[44]Liu, Y.F., Jiang, Z.L., 2013. Concept of non-ablative thermal protection system for hypersonic vehicles. AIAA Journal, 51(3):584-590.

[45]Lu, H.B., Liu, W.Q., 2012a. Numerical investigation on properties of attack angle for an opposing jet thermal protection system. Chinese Physics B, 21(8):084401.

[46]Lu, H.B., Liu, W.Q., 2012b. Numerical simulation in influence of forward-facing cavity on aerodynamic heating of hypersonic vehicle. Procedia Engineering, 29: 4096-4100.

[47]Lu, H.B., Liu, W.Q., 2012c. Thermal protection efficiency of forward-facing cavity and opposing jet combinational configuration. Journal of Thermal Science, 21(4):342-347.

[48]Lu, H.B., Liu, W.Q., 2012d. Cooling efficiency investigation of forward-facing cavity and opposing jet combinatorial thermal protection system. Acta Physica Sinica, 61(6):064703 (in Chinese).

[49]Lu, H.B., Liu, W.Q., 2012e. Effect of cavity physical dimension on forward-facing cavity and opposing jet thermal protection system cooling efficiency. Journal of Aerospace Power, 27(12):2666-2672 (in Chinese).

[50]Lu, H.B., Liu, W.Q., 2013. Investigation of thermal protection system by forward-facing cavity and opposing jet combinatorial configuration. Chinese Journal of Aeronautics, 26(2):287-293.

[51]Lu, H.B., Liu, W.Q., 2014. Research on thermal protection mechanism of forward-facing cavity and opposing jet combinatorial thermal protection system. Heat and Mass Transfer, 50(4):449-456.

[52]Marley, C.D., Riggins, D.W., 2011. Numerical study of novel drag reduction techniques for hypersonic blunt bodies. AIAA Journal, 49(9):1871-1882.

[53]Mehta, R.C., 2000. Peak heating for reattachment of separated flow on a spiked blunt-body. Heat and Mass Transfer, 36(4):277-283.

[54]Meyer, B., Nelson, H.F., Riggins, D., 2001. Hypersonic drag and heat-transfer reduction using a forward-facing jet. Journal of Aircraft, 38(4):680-684.

[55]Ohtake, K., 1998. Thermal analysis of the thermal protection system for the re-entry vehicle. Computer Methods in Applied Mechanics and Engineering, 151(3-4):301-310.

[56]Panaras, A.G., Drikakis, D., 2009. High-speed unsteady flows around spiked-blunt bodies. Journal of Fluid Mechanics, 632:69-96.

[57]Pezzella, G., 2012. Aerodynamic and aerothermodynamic design of future launchers preparatory program concepts. Aerospace Science and Technology, 23(1):233-249.

[58]Rong, Y.S., 2013. Drag reduction research in supersonic flow with opposing jet. Acta Astronautica, 91:1-7.

[59]Rong, Y.S., Liu, W.Q., 2010. Influence of opposing jet on flow field and aerodynamic heating at nose of a reentry vehicle. Acta Aeronautica Et Astronautica Sinica, 31(8):1552-1557 (in Chinese).

[60]Saravanan, S., Jagadeesh, G., Reddy, K.P.J., 2009. Investigation of missile-shaped body with forward-facing cavity at Mach 8. Journal of Spacecraft and Rockets, 46(3):577-591.

[61]Shang, J.S., 2002. Plasma injection for hypersonic blunt-body drag reduction. AIAA Journal, 40(6):1178-1186.

[62]Shang, J.S., Hayes, J., Menart, J., 2002. Hypersonic flow over a blunt body with plasma injection. Journal of Spacecraft and Rockets, 39(3):367-375.

[63]Silton, S.I., Goldstein, D.B., 2005. Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow. Journal of Fluid Mechanics, 528:297-321.

[64]Sriram, R., Jagadeesh, G., 2009. Film cooling at hypersonic Mach numbers using forward facing array of micro-jets. International Journal of Heat and Mass Transfer, 52(15-16):3654-3664.

[65]Tian, T., Yan, C., 2008. Numerical simulation on opposing jet in hypersonic flow. Journal of Beijing University of Aeronautics and Astronautics, 34(1):9-12 (in Chinese).

[66]Venukumar, B., Reddy, K.P.J., 2007. Experimental investigation of drag reduction by forward facing high speed gas jet for a large angle blunt cone at Mach 8. Sādhanā, 32:123-131.

[67]Venukumar, B., Jagadeesh, G., Reddy, K.P.J., 2006. Counterflow drag reduction by supersonic jet for a blunt body in hypersonic flow. Physics of Fluids, 18(11):118104.

[68]Wang, X., Pei, X., Chen, Z.M., et al., 2010. Supersonic with counter-flowing jets on drag and heat-transfer reduction. Journal of Propulsion Technology, 31(3):261-264 (in Chinese).

[69]Wang, Z.Q., Lv, H.Q., Lei, H.S., 2010. A numerical analysis of protection of blunt leading edge from aerodynamic heating by opposed jet. Journal of Astronautics, 31(5):1266-1271 (in Chinese).

[70]Yadav, R., Guven, U., 2014. Aerothermodynamics of a hypersonic vehicle with a forward-facing parabolic cavity at nose. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 228(10):1863-1874.

[71]Zheng, Y., Ahmed, N.A., Zhang, W., 2012. Heat dissipation using minimum counter flow jet ejection during spacecraft re-entry. Procedia Engineering, 49:271-279.

[72]Zhou, C.Y., Ji, W.Y., 2014. A three-dimensional numerical investigation on drag reduction of a supersonic spherical body with an opposing jet. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 228(2):163-177.

[73]Zhou, C.Y., Ji, W.Y., Zhang, X.W., et al., 2012. Numerical investigation on counter-flow jet drag reduction of a bluff body in supersonic flow. Chinese Journal of Applied Mechanics, 29(2):159-163 (in Chinese).

[74]Zhou, C.Y., Ji, W.Y., Zhang, X.W., et al., 2013. Numerical investigation on counter-flow jet drag reduction of a spherical body. Engineering Mechanics, 30(1):441-447 (in Chinese).