Response of a compressible, turbulent boundary layer to a short region of surface curvature

David Degani, Alexander J. Smits

Research output: Contribution to journalArticle

6 Scopus citations

Abstract

Calculations were performed to investigate the supersonic flow of a turbulent boundary layer over short regions of concave surface curvature. Upstream of each curved surface the freestream Mach number was 2.9. Three different constant radii of curvature models were investigated to cover a range of curvatures and turning angles. The numerical technique solved the full, Reynolds-averaged Navier-Stokes equations using two different turbulence models: algebraic eddy viscosity model and a one-equation model. The calculations were compared with recent experimental data and the agreement was surprisingly good, especially for the computations using the one-equation model.

Original languageEnglish (US)
Pages (from-to)23-28
Number of pages6
JournalAIAA journal
Volume27
Issue number1
DOIs
StatePublished - Jan 1989

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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