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Investigation on the opposing jet penetration mode transition mechanism in the hypersonic flow

Published online by Cambridge University Press:  21 June 2023

L. Long ,
B. Liu ,
Y.-s. Meng ,
W. Huang Open the ORCID record for W. Huang [Opens in a new window] ,
S.-b. Li  and
S.-s. Tian
L. Long
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China
B. Liu
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China
Y.-s. Meng
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China
W. Huang*
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China
S.-b. Li
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China
S.-s. Tian
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, People’s Republic of China
*
Corresponding author: W. Huang; Email: gladrain2001@163.com
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Abstract

As an effective drag reduction and thermal protection technology, the opposing jet can guarantee the flight safety of the hypersonic vehicle. In this paper, the jet mode transition is realised by controlling the total jet pressure ratio value (PR) with a function. The jet mode transition from the long penetration mode (LPM) to the short penetration mode (SPM) uses an increasing function. However, the jet mode transition from SPM to LPM uses a decreasing function. The flow field reconstruction process of a two-dimensional axisymmetric blunt body model in the hypersonic flow is studied when the jet mode transition between SPM and LPM changes into each other. The flow field structures and wall parameters of the LPM and SPM transition processes are obtained. The results indicate that the drag and Stanton number both decrease in the transition stage from LPM to SPM, and this is beneficial for the improvement of the drag reduction and thermal protection effect. The peak values of drag and Stanton number fall by 36.39% and 46.40%, respectively. When the jet mode transforms from SPM to LPM, the Stanton number increases, and the drag force first increases and then decreases. However, the final drag reduction effect is not obvious. With the increase in the change rate of the total pressure ratio of the two jet transformation modes, the jet mode transition time is advanced, and the flow field changes more violently.

Keywords

Opposing jetTotal jet pressure ratioLong penetration modeShort penetration modeMode transition
Type
Research Article
Information
The Aeronautical Journal , Volume 127 , Issue 1317 , November 2023 , pp. 2047 - 2065
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Copyright
© The Author(s), 2023. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Antonio, V. and Giuseppe, P. Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles. Switzerland: Springer International Publishing, 2015.Google Scholar
Peng, W.-j. The Engineering Method of Aerodynamic Heating over Projectiles ’Head at Hypersonic Flow and Numerical Heat Transfer. Nanjing University of Science and Technology, 2010.Google Scholar
Zheng, Y.-y. and Ahmed, N.A. Thermal protection systems spacecraft re-entry-a brief overview, Int J Heat Mass Transf, 2013, 8, (1), pp 99–118.Google Scholar
Gerdroodbary, M.B. Aerodynamic Heating in Supersonic and Hypersonic Flows: Advanced Techniques for Drag and Aero-Heating Reduction. Elsevier, 2022.Google Scholar
Huang, J. and Yao, W. High temperature mechanical properties of strain-isolation-pad for thermal protection system, J Spacecr Rockets, 2018, 55, (4), pp 848–855.CrossRefGoogle Scholar
Lu, Q., Jiang, G.-q., Luo, X.-g. and Hu, L.-f. Lightweight and non-ablation new TPS for X-37B aerospace vehicle, Modern Defence Technol, 2012, 40, (1), pp 16–20.Google Scholar
Ma, X.-p., Guo, Y.-l. and Zhang, Y. Progression of lightweight ablative thermal protection materials, Space Manufact Technol, 2018, (1), pp 2–6.Google Scholar
Hassanvand, A., Gerdroodbary, M.B. and Abazari, A.M. Injection of hydrogen sonic multi-jet on inclined surface at supersonic flow. International Journal of Modern Physics C, 2021, 32(3), p 2150043.CrossRefGoogle Scholar
Pish, F., Man, H.T.D., Gerdroodbary, M.B., Nam, N.D., Moradi, R., Babazadeh, H. Computational Study of the cavity flow over sharp nose cone in supersonic flow. International Journal of Modern Physics C, 2020, 31(6), p 2050079.CrossRefGoogle Scholar
Ladoon, D.W., Schneider, S.P., Schmisseur, J-d. Physics of Resonance in a Supersonic Forward-Facing Cavity. Journal of Spacecraft and Rockets, 1998, 35, (5), pp 626–632.CrossRefGoogle Scholar
Shashank, K. and Kojiro, S. Assessment of aerodynamic effectiveness for aerospike application on hypothesized lifting-body in hypersonic flow, 31st AIAA Applied Aerodynamics Conference, 2013, San Diego, CA.Google Scholar
Gerdroodbary, M.B. and Hosseinalipour, S.M. Numerical simulation of hypersonic flow over highly blunted cones with spike, Acta Astronaut, 2010, 67, pp 180–193.CrossRefGoogle Scholar
Zhang, R.-r. Investigation of Drag and Heat Flux Reduction Mechanism of the Counterflowing Pulsed Jet and Its Combinations on Aerospace Vehicles. National University of Defense Technology, 2018.Google Scholar
Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Experimental investigation on spiked body in hypersonic flow, Aeronaut J, 2008, 112, (1136), pp 593–598.CrossRefGoogle Scholar
Pish, F., Moradi, R., Edalatpour, A. and Gerdroodbary, M.B. The effect of coolant injection from the tip of spike on aerodynamic heating of nose cone at supersonic flow, Acta Astronaut, 2019, 154, pp 52–60.CrossRefGoogle Scholar
Huang, W. A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations. J. Zhejiang Univ. Sci A, 2015, 16, (7), pp 551–561.CrossRefGoogle Scholar
Gerdroodbary, M.B. Numerical analysis on cooling performance of counterflowing jet over aerodisked blunt body, Shock Waves, 2014, 24, (5), pp 537–543.CrossRefGoogle Scholar
Ou, M., Yan, L., Huang, W., Li, S.B. and Li, L.Q. Detailed parametric investigations on drag and heat flux reduction induced by a combinational spike and opposing jet concept in hypersonic flows, Int J Heat Mass Transf, 2018, 126, pp 10–31.CrossRefGoogle Scholar
Huang, W., Chen, Z., Yan, L., Yan, B.B. and Du, Z.B. Drag and heat flux reduction mechanism induced by the spike and its combinations in supersonic flows: A review, Prog Aerosp Sci, 2019, 105, pp 31–39.CrossRefGoogle Scholar
Love, E.S. The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow, NACA, 1952, RM L52119a.Google Scholar
Finley, P.J. The flow of a jet from a body opposing a supersonic free stream, J Fluid Mech, 1966, 26, (2), pp 337–368.CrossRefGoogle Scholar
Shahab, E.V. and Sarallah, A. Hypersonic drag and heat reduction mechanism of a new hybridmethod of spike, multi-row discs and opposing jets aerodynamic configuration, Int. J. Heat Mass Trans, 2022, 194, pp 123–134.Google Scholar
Zhu, L., Li, W.-x., Tian, X.-t., Song, J. and Hu, B.-w. Establishment process of spiked lateral jet in hypersonic flows, Aerosp Sci Technol, 2022, 315, pp 107–507.Google Scholar
Xie, W., Luo, Z.-b., Hou, L., Zhou, Y., Liu, Q. and Peng, W.-q. Characterization of plasma synthetic jet actuator with Laval-shaped exit and application to drag reduction in supersonic flow, Phys Fluids, 2021, 33, pp 191–104.CrossRefGoogle Scholar
Zhang, W.-q., Wang, X.-w., Zhang, Z.-j., Han, F., Zhao, S.-s. Heat and drag reduction of single and combined opposing jets in hypersonic nonequilibrium flows, Aerosp Sci Technol, 2021, 310, pp 107–194.Google Scholar
Ji, C., Liu, B., Huang, W., Li, S.-b. and Yan, L. Investigation on the drag reduction and thermal protection properties of the porous opposing jet in the supersonic flow: A parametric study with constant mass flow rate, Aerosp Sci Technol, 2021, 118, 107–164.CrossRefGoogle Scholar
Sun, X.-w., Guo, Z.-y., Huang, W., Li, S.-b. and Yan, L. Drag and heat reduction mechanism induced by a combinational novel cavity and counterflowing jet concept in hypersonic flows, Acta Astronaut, 2016, 126, pp 109–119.CrossRefGoogle Scholar
Sudarshan, B., Rao, S.M.V., Jagadeesh, G. and Saravanan, S. Effect of the axial cavity with an opposing high-pressure jet combination in a Mach 6 flow condition, Acta Astronaut, 2021, 178, pp 335–348.CrossRefGoogle Scholar
Huang, J. and Yao, W.-x. A novel non-ablative thermal protection system with combined spike and opposing jet concept, Acta Astronaut, 2019, 159, pp 41–48.CrossRefGoogle Scholar
Shang, J.S. and Hayes, K. Jet-spike bifurcation in high-speed flows, AIAA J, 2001, 39, (6), pp 1159–1165.CrossRefGoogle Scholar
Demetriades, A. and Hopkins, A.T. Asymmetric shock-wave oscillations on spiked bodies of revolution, J Spacecr Rockets, 1976, 13, (11), pp 703–704.CrossRefGoogle Scholar
Reding, J.P. Fluctuating pressures on mildly indented nosetips, J Spacecr Rockets, 1979, 16, (5), pp 302–310.CrossRefGoogle Scholar
Romeo, D.J. and Sterrett, J.-r. Exploratory investigation of the effect of a forward-facing jet on the bow shock of a blunt body in a Mach 6 free stream, NASA TN D-1605, 1963.Google Scholar
Romeo, D.J. and Sterrett, J.-r. Flowfield for sonic jet exhausting counter to hypersonic mainstream, AIAA J, 1965, 3, (3), pp 544–546.CrossRefGoogle Scholar
Philip, O. and Richard, H. The effects of retrorockets on the aerodynamic characteristics of conical aeroshell plaetary entry vehicles, AIAA J, 1970, 10, pp 70–219.Google Scholar
Hayashi, K. and Aso, S. Effect of pressure ratio on aerodynamic heating reduction due to opposing jet, 33rd AIAA Fluid Dynamic Conference and Exhibit, 2003.CrossRefGoogle Scholar
Hayashi, K., Aso, S. and Tani, Y. Experimental study on thermal protection system by opposing jet in supersonic flow, J Spacecr Rockets, 2006, 43, (1), pp 233–236.CrossRefGoogle Scholar
Shen, B. and Liu, W. Thermal protection performance of a low pressure short penetration mode in opposing jet and its application, Int J Heat Mass Transf, 2020, 163, pp 12–466.CrossRefGoogle Scholar
Sriram, R. and Jagadeesh, G. Film cooling at hypersonic mach numbers using forward facing array of micro-jets, Int J Heat Mass Transf, 2009, 52, pp 3654–3664.CrossRefGoogle Scholar
Karpman, I.M. Outflow of an unexpanded jet into counter supersonic sand subsonic flows. Fluid Dynam, 1977, 12, pp 73–79.CrossRefGoogle Scholar
Venkatachari, B.S., Cheng, G.C. and Chang, C. Effect of counter flowing jet on supersonic slender-body configurations: A numerical study, J Spacecr Rockets, 2020, 57, (6), pp 1204–1221.CrossRefGoogle Scholar
Deng, F., Xie, F., Huang, W., Dong, H. and Zhang, D. Numerical exploration on jet oscillation mechanism of counterflowing jet ahead of a hypersonic lifting-body vehicle. Sci China Technol Sci, 2018, 61, (7), pp 1056–1071.CrossRefGoogle Scholar
Lee, J., Lee, H.J. and Huh, H. Drag reduction analysis of counterflow jets in a short penetration mode. Aerosp Sci Technol, 2020, 106, pp 106–165.CrossRefGoogle Scholar
Venkatachari, B.S., Mullane, M. and Cheng, G. Numerical study of counterflowing jet effects on supersonic slender-body configurations, 33rd AIAA Applied Aerodynamics Conference, 2015.CrossRefGoogle Scholar
Kim, Y.C., Roh, T.S., Huh, H. and Lee, HJ. Study on the combined effect of various injection conditions on the drag reduction by a counter-flow jet in supersonic flow, Aerosp Sci Technol, 2020, 98, pp 105–580.CrossRefGoogle Scholar
Bibi, A., Maqsood, A., Sherbaz, S., and Dala, L. Drag reduction of supersonic blunt bodies using opposing jet and nozzle geometric variations, Aerosp Sci Technol, 2017, 69, pp 244–256.CrossRefGoogle Scholar
Huang, J., Yao, W. and Jiang, Z. Penetration mode effect on thermal protection system by opposing jet. Acta Astronaut, 2019, 160, pp 206–215.CrossRefGoogle Scholar
Wang, Z. and Zhang, X. Parametric research on drag reduction and thermal protection of blunt-body with opposing jets of forward convergent nozzle in supersonic flows, Acta Astronaut, 2022, 190, pp 218–230.CrossRefGoogle Scholar
Li, S.-b., Wang, Z.-g., Huang, W., and Liu, J. Effect of the injector configuration for opposing jet on the drag and heat reduction, Aerosp Sci Technol, 2016, 51, pp 78–86.CrossRefGoogle Scholar
Li, S.-b., Wang, Z.-g., Huang, W. and Liu, J. Drag and heat reduction performance for an equal polygon opposing jet, J Aerosp Eng, 2017, 30, (1), p 04016065.CrossRefGoogle Scholar
Warren, C.H.E. An experimental investigation of the effect of ejecting a coolant gas at the nose of a bluff body, J Fluid Mech, 1960, 8, (3), pp 400–417.CrossRefGoogle Scholar
Zhang, R.-r., Huang, W., Yan, L., Li, L.-q., Li, S.-b., Moradi, R. Numerical investigation of drag and heat flux reduction mechanism of the pulsed counterflowing jet on a blunt body in supersonic flows, Acta Astronautica, 2018, 146, pp 123–133.CrossRefGoogle Scholar
Zhang, R.-r., Huang, W., Li, L.-q., Chen, Z. and Moradi, R. Drag and heat flux reduction induced by the pulsed counterflowing jet with different periods on a blunt body in supersonic flows, Int J Heat Mass Transf, 2018, 127, pp 503–512.CrossRefGoogle Scholar
Zhang, R.-r., Huang, W., Yan, L., Chen, Z. and Moradi, R. Drag and heat flux reduction induced by the pulsed counterflowing jet with different waveforms on a blunt body in supersonic flows, Acta Astronaut, 2019, 160, pp 635–645.CrossRefGoogle Scholar