Turbulent Shear Stress Measurement in Hypersonic Flow
Abstract
The present report refers to the experimental evaluation of additional shear stress terms which might be significant at high Mach numbers. These terms are necessary to develop accurate empirical turbulence models to be used in Navier-Stokes computational codes. The measurement technique used was the simultaneous employment of hot wire anemometers in conjunction with laser doppler velocimeters to obtain density-velocity triple correlation terms and compressible shear stress distribution at Mach 6. This diagnostic tool is available for measurements of turbulent hypersonic flows. Comparisons of present laser velocimeter turbulence measurements with previous hot wire results indicate that significant errors can be incurred in hypersonic flows with the old standard techniques. Results indicate that adequate particle tracking is possible at Mach 6. Keywords: Boundary layer; Hypersonic flow; Turbulent stresses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1989
- Accession Number
- ADA206453
Entities
People
- F. K. Owen
- Wladimiro Calarese