Advertisement

Shock Waves pp 251-256 | Cite as

Real gas effects on flows over rearward-facing steps in high enthalpy flows

  • M. J. Hayne
  • S. L. Gai
  • D. J. Mee
  • R. G. Morgan
Conference paper

Abstract

The University of Queensland has several test facilities (T4, X2, X3) capable of conducting tests over a large range of flow enthalpies. In the hypersonic limit, the parameters that must be matched to correlate the heat transfer distributions downstream of the step are the hypersonic viscous interaction parameter \( \bar V^* _{\infty L} \), the hypersonic small disturbance parameter M∞ τ, and the Damköhler number, Ω. Matching \( \bar V^* _{\infty L} \) and M∞ τ the Damköhler number was varied between two flow conditions with enthalpies of 5.6 MJ/kg and 26.0 MJ/kg. This was done in order to determine what differences existed between the measured heat transfer rates at the two enthalpies. The results indicated, that even though the Damköhler numbers varied between the two flow conditions, the flows remained chemically frozen, with the heat transfer distributions agreeing to within experimental uncertainty.

Keywords

Heat Transfer Rate Shock Tube Damkohler Number Stanton Number Shock Tunnel 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    S.L. Gai, N.T. Reynolds, C. Ross and J.P. Baird: Measurements of heat transfer in separated high-enthalpy dissociated laminar hypersonic flow behind a step. Journal of Fluid Mechanics 199, 541 (1989)ADSCrossRefGoogle Scholar
  2. 2.
    M. Hayne: Hypervelocity Flow Over Rearward-Facing Steps. PhD Thesis, The University of Queensland (2004)Google Scholar
  3. 3.
    G.D. Walberg: Hypersonic flight experience. Philosophical Transcriptions of the Royal Society of London A 335, 91 (1991)ADSCrossRefGoogle Scholar
  4. 4.
    S.L. Gai: Flow behind a step in high enthalpy hypersonic flow. Unpublished (2001)Google Scholar
  5. 5.
    R. Morgan: ‘Free-piston Driven Expansion Tubes’. In: Handbook of Shock Waves, ed. by G. Ben-Dor, O. Igra and T. Elperin, (Academic Press, San Diego, 2001) pp. 603–622CrossRefGoogle Scholar
  6. 6.
    R. Morgan: ‘Free Piston-Driven Reflected Shock Tunnels’. In: Handbook of Shock Waves. ed. by G. Ben-Dor, O. Igra and T. Elperin, (Academic Press, San Diego, 2001) pp. 587–601CrossRefGoogle Scholar
  7. 7.
    P. Jacobs: Quasi-one-dimensional modeling of a free-piston shock tunnel. AIAA Journal 32(1), 137 (1994)ADSMathSciNetCrossRefGoogle Scholar
  8. 8.
    M. McIntosh: A computer program for the numerical calculation of equilibrium and perfect gas conditions in shock tunnels. Tech. Rep. CPD 169, Australian Defence Scientific Service (1968)Google Scholar
  9. 9.
    M. Mcintosh: Computer programmes for supersonic real gas dynamics. Tech. Rep. WRETN-180, Australian Defence Scientific Service(1970)Google Scholar
  10. 10.
    D. Shultz and T. Jones: Heat-transfer measurements in short-duration hypersonic facilities. AGARDograph 165 (1973)Google Scholar
  11. 11.
    P.M. Chung: Chemically reacting nonequilibrium boundary layers. Advances in Heat Transfer 2, 109 (1965)CrossRefGoogle Scholar
  12. 12.
    R. East, R. Stalker and J. Baird: Measurements of heat transfer to a flat plate in a dissociated high-enthalpy laminar air flow. Journal of Fluid Mechanics 97(4), 673 (1980)ADSCrossRefGoogle Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • M. J. Hayne
    • 1
  • S. L. Gai
    • 2
  • D. J. Mee
    • 1
  • R. G. Morgan
    • 1
  1. 1.Centre for Hypersonics, Department of Mechanical EngineeringThe University of QueenslandAustralia
  2. 2.School of Aerospace and Mechanical EngineeringUniversity College, UNSW@ADFACanberraAustralia

Personalised recommendations