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Numerical Study of Heat Transfer on Confined Under-Expanded Impinging Jet from Slot into a Plenum

  • Tinglong Huang
  • Lianjie YueEmail author
  • Xinyu Chang
Conference paper

Abstract

The aerodynamic thermal loads on under-expanded jet from bleed slot into a plenum are obtained at different conditions. It grossly differs from the unconfined impinging jet due to the appearance of left-confined wall. The numerical results show that at low slot angle, heat flux along impinging wall peaks twice due to the stagnation of high enthalpy flow and the shock wave/boundary layer interactions, whereas only one peak occurs at higher slot angle due to the former mechanism. When impingement angle is larger than 50°, the highest thermal loads change a little. As the impingement height increases, the overall aerodynamic thermal loads decrease at the same freestream conditions. Generally, it is the confined wall that makes the flow behind the plate shock supersonic, which allows the SWBLIs to occur.

References

  1. 1.
    J. Häberle, A. Gülhan, Experimental investigation of a two-dimensional and a three-dimensional scramjet inlet at Mach 7. J. Propuls. Power 24(2008–09), 1023–1034 (2008)CrossRefGoogle Scholar
  2. 2.
    T. Kouchi, T. Mitani, G. Masuya, Numerical simulations in scramjet combustion with boundary-layer bleeding. J. Propuls. Power 21(4), 642–649 (2012)CrossRefGoogle Scholar
  3. 3.
    L. Yue et al., Aerothermal characteristics of bleed slot in hypersonic flows. Sci. China Phys. Mech. Astron. 58(10), 1–14 (2015)CrossRefGoogle Scholar
  4. 4.
    C.D. Donaldson, R.S. Snedeker, A study of free jet impingement. Part 1. Mean properties of free and impinging jets. J. Fluid Mech 45(2), 281–319 (1971)CrossRefGoogle Scholar
  5. 5.
    D. Schulte, A. Henckels, U. Wepler, Reduction of shock induced boundary layer separation in hypersonic inlets using bleed. Aerosp. Sci. Technol. 2(4), 231–239 (1998)CrossRefGoogle Scholar
  6. 6.
    B. Henderson, J. Bridges, M. Wernet, An experimental study of the oscillatory flow structure of tone-producing supersonic impinging jets. J. Fluid Mech. 542, 115–137 (2005)CrossRefGoogle Scholar
  7. 7.
    F. Alvi, J. Ladd, W. Bower, Experimental and computational investigation of supersonic impinging jets. AIAA J. 40(4), 599–609 (2002)CrossRefGoogle Scholar
  8. 8.
    F. Alvi, K. Iyer, Mean and unsteady flowfield properties of supersonic impinging jets with lift plates. AIAA paper 1829, 1999 (1999)Google Scholar
  9. 9.
    G. Kalghatgi, B. Hunt, Occurrence of stagnation bubbles in supersonic jet impingement flows. Aeronaut. Q. 27, 169–185 (1976)CrossRefGoogle Scholar
  10. 10.
    Y. Nakai, N. Fujimatsu, K. Fujii, Experimental study of underexpanded supersonic jet impingement on an inclined flat plate. AIAA J. 44(11), 2691–2699 (2006)CrossRefGoogle Scholar
  11. 11.
    J. Song et al., Thermal characteristics of inclined plate impinged by underexpanded sonic jet. Int. J. Heat Mass Transf. 62, 223–229 (2013)CrossRefGoogle Scholar
  12. 12.
    H. Lu, L. Yue, X. Chang, Flow characteristics of hypersonic inlets with different cowl-lip blunting methods. Sci. China Phys. Mech. Astron. 57(4), 741–752 (2014)CrossRefGoogle Scholar
  13. 13.
    H. Lu et al., Interaction of isentropic compression waves with a bow shock. AIAA J. 51(10), 2474–2484 (2013)CrossRefGoogle Scholar
  14. 14.
    J. Häberle, A. Gülhan, Internal flowfield investigation of a hypersonic inlet at Mach 6 with bleed. J. Propuls. Power 23(2007–10), 1007–1017 (2007)CrossRefGoogle Scholar
  15. 15.
    T. Mitani et al., Boundary-layer control in Mach 4 and Mach 6 scramjet engines. J. Propuls. Power 21(4), 636–641 (2005)CrossRefGoogle Scholar

Copyright information

© Springer International Publishing AG, part of Springer Nature 2019

Authors and Affiliations

  1. 1.Institute of Mechanics, Chinese Academy of SciencesBeijingChina

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