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Research on thermal protection mechanism of forward-facing cavity and opposing jet combinatorial thermal protection system

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Abstract

Validated by the correlated experiments, a nose-tip with forward-facing cavity/opposing jet/the combinatorial configuration of forward-facing cavity and opposing jet thermal protection system (TPS) are investigated numerically. The physical mechanism of these TPS is discussed, and the cooling efficiency of them is compared. The combinatorial system is more suitable to be the TPS for the high speed vehicles which need fly under various flow conditions with long-range and long time.

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References

  1. Zhang F, Liu WQ (2007) Analysis of thermal wrinkling resulted from non-uniform temperature distribution in transpiration cooling formed platelets. Acta Aeronaut et Astronaut Sinica 28(1):138 (in Chinese)

    Google Scholar 

  2. Ye H, Geng X (2011) The feasibility analysis of the application of TPV system in reentry. Sci China Tech Sci 41(1):102 (in Chinese)

    Google Scholar 

  3. Glass DE (2006) Heat-pipe-cooled leading edges for hypersonic vehicles. NASA Langley Research Center July 12–13

  4. Hartmann J, Troll B (1922) On a new method for the generation of sound waves. Phys Rev 20(6):719

    Article  Google Scholar 

  5. Engblom WA, Goldstein DB (1997) Fluid dynamics of hypersonic forward-facing cavity flow. J Spacecr Rocket 34(4):437

    Article  Google Scholar 

  6. Rifki R, Ahmed A (2009) Flowfield of a forward-facing shaped-charge cavity. J Aircraft 46(3):1059

    Article  Google Scholar 

  7. Burbank PB, Stallings RL (1959) Heat-transfer and pressure measurements on a flat nose cylinder at a mach number range of 2.49 to 4.44. NASA TM X-221

  8. Yuceil B, Dolling DS, Wilson D (1993) A preliminary investigation of the helmholtz resonator concept for heat flux reduction. AIAA 1993-2742

  9. Engblom WA, Golsatein DB (1996) Nose-tip surface heat reduction mechanism. AIAA 96-0354

  10. Seiler F, Srulijes J, Pastor MG, et al (2007) Heat fluxes inside a cavity placed at the nose of a projectile measured in a shock tunnel at mach 4.5. New Res. in Num. and Exp. Fluid Mech. VI, NNFM96:309

  11. Saravanan S, Nagashetty K, Jagadeesh G, et al (2007) Experimental investigation of heat transfer reduction using forward facing cavity for missile shaped bodies flying at hypersonic speed. In: 26th international symposium on shock waves, part VIII: 316

  12. Saravanan S, Jagadeesh G, Reddy KPJ (2009) Investigation of missile-shaped body with forward-facing cavity at mach 8. J Spacecr Rocket 46(3):577

    Article  Google Scholar 

  13. Warren CHE (1960) An experimental investigation of the effect of ejecting a coolant gas at the nose of a bluff body. J Fluid Mech 8(3):400

    Article  Google Scholar 

  14. Aso S, Hayashi K, Mizoguchi M (2002) A study on aerodynamic heating reduction due to opposing jet in hypersonic flow. AIAA 2002-0646

  15. Hayashi K, Aso S (2003) Effect of pressure ratio on aerodynamic heating reduction due to opposing jet. AIAA 2003-4041

  16. Hayashi K, Aso S, Tani Y (2005) Numerical study of thermal protection system by opposing jet. AIAA 2005-188

  17. Tian T, Yan C (2008) Numerical simulation on opposing jet in hypersonic flow. J Beijing Univ Aero Astron 34(1):9 (in Chinese)

    Google Scholar 

  18. Tamada I, Aso S, Tani Y (2010) Reducing aerodynamic heating by the opposing jet in supersonic and hypersonic flows. AIAA 2010-991

  19. Yan C (2006) Computational fluid dynamics methodology and application. Beijing University of Aeronautics and Astronautics Press, Beijing (in Chinese)

    Google Scholar 

  20. Tao WQ (2001) Numerical heat transfer, 2nd edn. Xi’an Jiaotong University Press, Xi’an (in Chinese)

    Google Scholar 

  21. Azevedo JLF, Heidi K (1998) Comparison of unstructured grid finite volume methods for cold gas hypersonic flow simulations. AIAA 98-2629

  22. Wang CY (2000) Computational fluid dynamics and parallel algorithm. National University of Defense Technology Press, Changsha (in Chinese)

    Google Scholar 

  23. Baker AJ (1980) Numerical grid generation techques. NASA CP-2166

  24. Middelcoff JF, Thomas PD (1979) Direct control of the grid point distribution in meshes generated by elliptic equations. AIAA 1979-1462

  25. Chang KS, Choi CJ (1986) Separeted laminar natural convection above a horizontal isothermal square cylinder. Int Commun Heat Mass Transf 13(2):201

    Article  Google Scholar 

Download references

Acknowledgments

This work was supported by the Major Program of National Natural Science Foundation of China (Grant No. 90916018) and the Research Fund for the Doctoral Program of Higher Education of China (Grant No. 200899980006).

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Authors and Affiliations

  1. Science and Technology on Scramjet Laboratory, College of Aerospace and Material Engineering, National University of Defense Technology, Changsha, 410073, Hunan, China

    Hai-Bo Lu & Wei-Qiang Liu

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  1. Hai-Bo Lu
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  2. Wei-Qiang Liu
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Correspondence to Hai-Bo Lu.

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Lu, HB., Liu, WQ. Research on thermal protection mechanism of forward-facing cavity and opposing jet combinatorial thermal protection system. Heat Mass Transfer 50, 449–456 (2014). https://doi.org/10.1007/s00231-013-1247-3

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  • DOI: https://doi.org/10.1007/s00231-013-1247-3

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