Fluctuation heat transfer in shock wave/turbulent boundary- layer interaction

M. Hayashi, S. Aso, A. Tan

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Abstract

A new high resolution, fast response, heat flux sensor was used to measure heat fluxes in the interaction regions of oblique incident shock waves and turbulent boundary layers. Experiments were conducted in a wind tunnel using the multi- layered thin-film heat-transfer gauge for a Mach number 4, wall temperature condition Tw/TO of 0.56, and Reynolds number of 1.26 x 107. Measurements were made for both unseparated and separated boundary layer conditions. For the case of an unseparated boundary layer, heat flux fluctuations became strong near the impingement point of the incident shock wave, and no intermittency phenomenon was observed. For the case of a separated boundary layer, significant fluctuations of heat flux were observed throughout the interaction region. These fluctuations were very strong, especially near the separation and reattachment points. Near the separation point, intermittency of heat transfer was observed. (J.M.M.)

Original languageEnglish
Pages (from-to)339-404
Number of pages66
JournalAIAA J.
Volume27
Issue number4 , Apr., 1989
Publication statusPublished - Jan 1 1989

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All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Hayashi, M., Aso, S., & Tan, A. (1989). Fluctuation heat transfer in shock wave/turbulent boundary- layer interaction. AIAA J., 27(4 , Apr., 1989), 339-404.