Hostname: page-component-cd9895bd7-gvvz8 Total loading time: 0 Render date: 2024-12-19T10:34:30.008Z Has data issue: false hasContentIssue false
  • English
  • Français

Measurements of heat transfer to a flat plate in a dissociated high-enthalpy laminar air flow

Published online by Cambridge University Press:  19 April 2006

R. A. East ,
R. J. Stalker  and
J. P. Baird
R. A. East
Affiliation:
Department of Aeronautics & Astronautics, University of Southampton, U.K.
R. J. Stalker
Affiliation:
Department of Mechanical Engineering,
Previously at the Department of Physics, School of General Studies, Australia National University, Canberra.
University of Queensland, Brisbane, Australia
J. P. Baird
Affiliation:
Department of Physics, School of General Studies, Australian National University, Canberra, Australia
Get access Rights & Permissions [Opens in a new window]

Abstract

Heat-transfer rates from a non-equilibrium hypersonic air flow to flat plates at zero and 12° incidence have been measured in a free piston shock tunnel at stagnation enthalpy levels up to 51 MJ kg−1. Nozzle flow conditions resulted in test section velocities up to 8·1 km 8−1 and in an experimental regime in which the free stream was chemically frozen and the flat-plate boundary layer was laminar. Estimates of the gas-phase and surface-reaction Damkohler numbers have been made and the heat-transfer results are discussed in this context. At the highest test-section densities non-equilibrium endothermic gas phase reactions involving oxygen atoms in the boundary layer are suggested as a possible mechanism for the observed low heattransfer rates.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 97 , Issue 4 , 29 April 1980 , pp. 673 - 699
Copyright
© 1980 Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Bauer, E. & Zlotnick, M. 1959 Transport coefficients of air to 8000 K. ARS J. 29, 721–728.Google Scholar
Bray, K. N. C. 1970 Non-equilibrium flow problems of space shuttles. Aero. Res. Counc. Rep. 32, 408.Google Scholar
Breshears, W. D. & Bird, P. F. 1968 J. Chem. Phys. 48, 4678–4683.
Chung, P. M. 1965 Chemically reacting non-equilibrium boundary layers. Advances in Heat Transfer, vol. II, pp. 109–270. Academic.
Crane, K. C. A. 1975 Mass spectrometry in pulsed hypersonic flows. Ph.D. thesis, Australian National University.
Davies, L. & Wilson, J. L. 1969 Influence of reflected shock and boundary layer interaction on shock tube flows. Phys. Fluids Suppl. 12, I 37–43.Google Scholar
Davies, W. R. & Bernstein, L. 1969 Heat transfer and transition to turbulence in the shock-induced boundary layer on a semi-infinite flat plate. J. Fluid Mech. 36, 87–112.Google Scholar
Dorrance, W. H. 1962 Viscous hypersonic flow. McGraw-Hill.
East, R. A., Stalker, R. J. & Baird, J. P. 1977 Laminar flat plate heat transfer measurements from a dissociated high enthalpy hypersonic airflow. Univ. of Southampton, Rep. AASU 338.
Hayes, W. D. & Probstein, R. F. 1959 Hypersonic Flow Theory. Academic Press.
Hirschfelder, J. O., Curtis, C. F. & Bird, R. B. 1954 Molecular Theory of Gases and Liquids. John Wiley.
Lordi, J. A., Mates, R. E. & Moselle, J. R. 1966 Computer program for the numerical solution of non-equilibrium expansion of reacting gas mixtures. N.A.S.A. Rep. NASA CR-472.
Lordi, J. A., Vidal, R. J. & Johnson, C. B. 1971 Chemical non-equilibrium effects on the flow in the windward plane of symmetry of a blunted delta orbiter. N.A.S.A. Rep. TMX 2508.
McCaffrey, B. J., East, R. A. & Stent, M. W. 1975 A thin film catalytic-non—catalytic heat transfer gauge for shock tube measurements in reacting gases. Univ. of Southampton, Rep. AASU 336.
Rosner, D. E. 1963 Scale effects and correlation in non-equilibrium convective heat transfer. A.I.A.A. J. 1, 1550–1555.Google Scholar
Schultz, D. L. & Jones, T. V. 1973 Heat transfer measurements in short-duration hypersonic facilities. AGARDograph 165.
Smith, C. E. 1966 The starting process in a hypersonic nozzle. J. Fluid Mech. 24, 625–640.Google Scholar
Stalker, R. J. 1972 Development of a hypervelocity wind tunnel. J. Roy. Aero. Soc. 76, 374–384.Google Scholar
Stalker, R. J. & Crane, K. C. A. 1978 Driver gas contamination in a high enthalpy reflected shock tunnel. A.I.A.A. J. 16, 277–279.Google Scholar
Stalker, R. J. & McIntosh, M. K. 1973 Hypersonic nozzle flow of air with high initial dissociation levels. J. Fluid Mech. 58, 749–761.Google Scholar
Stalker, R. J. & Stollery, J. L. 1975 The use of a Stalker tube for studying the high enthalpy non-equilibrium air flow over delta wings. In Modern Developments in Shock Tube Research. Japan: Shock Tube Research Society.
Vidal, R. J. & Golian, T. C. 1967 Heat transfer measurements with a catalytic flat plate in dissociated oxygen. A.I.A.A. J. 5, 1579–1588.Google Scholar