Supersonic turbulent boundary layer subjected to step changes in wall temperature

Jean François Debiève, Pierre Dupont, Douglas R. Smith, Alexander J. Smits

Research output: Contribution to journalArticle

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Abstract

An investigation has been made into the effect of a step change in wall temperature on a turbulent boundary layer in a supersonic flow at a Mach number of 2.3. Measurements of the mean and turbulent flowfields were made. The results show that the relaxation behavior in general is slow except near the wall where the logarithmic behavior of the thermal and dynamical field is unaffected. Perhaps more interestingly, it appears that the effect of strong heating on the velocity field can be explained largely in terms of changes induced in the local fluid properties, and specific compressibility effects appear to be small. A mixing length argument is suggested for scaling the Reynolds stresses and the comparison with measurements of the longitudinal Reynolds stress is encouraging.

Original languageEnglish (US)
Pages (from-to)51-57
Number of pages7
JournalAIAA journal
Volume35
Issue number1
DOIs
StatePublished - Jan 1 1997

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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    Debiève, J. F., Dupont, P., Smith, D. R., & Smits, A. J. (1997). Supersonic turbulent boundary layer subjected to step changes in wall temperature. AIAA journal, 35(1), 51-57. https://doi.org/10.2514/2.86