Hot-wire investigation of an unseparated shock-wave/turbulent boundary-layer interaction

K. Hayakawa, A. J. Smits, S. M. Bogdonoff

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22 Scopus citations


Detailed hot-wire measurements of the longitudinal component of the mass-flow fluctuations have been made for an adiabatic fully attached shock-wave/turbulent boundary-layer interaction. The shock wave is induced by an 8-deg compression corner at a Mach number of 2.85 and a unit Reynolds number of 6.3×107 m -l. The data indicate that the absolute mass-flow turbulence intensity increases abruptly through the shock wave, and continues to increase with further distance downstream. When nondimensionalized by the local freestream massflow rate the maximum turbulence intensity actually exceeds the upstream equilibrium value at the last measurement station. Measurements of the probability density of the fluctuations reveal only minor difference between the boundary-layer behavior upstream and downstream of the shock. A significant dip in the kurtosis was observed near the point of maximum intensity, which also coincided with the onset of intermittency.

Original languageEnglish (US)
Pages (from-to)579-585
Number of pages7
JournalAIAA journal
Issue number5
StatePublished - May 1984

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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