Mean flowfield scaling of supersonic shock-free three-dimensional turbulent boundary layer

W. Konrad, A. J. Smits, D. Knight

Research output: Contribution to journalArticle

5 Scopus citations

Abstract

The mean flowfield of a three-dimensional supersonic turbulent boundary layer, generated by a 20-deg isentropic compression, was studied experimentally and numerically. Experimental data include surface flow visualization, wall static pressures, surface skin friction, and surveys of pitot pressures, yaw angles, and static pressures. Earlier published comparisons with data computed from the three-dimensional Reynolds-averaged compressible Navier-Stokes equations with an algebraic turbulence eddy viscosity closure show good agreement within experimental and computational uncertainties. Focus of the current work is the presentation of different scalings of the experimental data and the proposal of a new model for the mean flowfield scaling. Comparison to a subsonic three-dimensional boundary layer is made for this new scaling law.

Original languageEnglish (US)
Pages (from-to)2120-2126
Number of pages7
JournalAIAA journal
Volume38
Issue number11
DOIs
StatePublished - Nov 2000

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Fingerprint Dive into the research topics of 'Mean flowfield scaling of supersonic shock-free three-dimensional turbulent boundary layer'. Together they form a unique fingerprint.

  • Cite this