Turbulent shear stresses in compressible boundary layers
Abstract
Hotwire anemometer measurements of turbulent shear stresses in a Mach 3 compressible boundary layer were performed in order to investigate the effects of heat transfer on turbulence. Measurements were obtained by an xprobe in a flat plate, zero pressure gradient, two dimensional boundary layer in a wind tunnel with wall to freestream temperature ratios of 0.94 and 0.71. The measured shear stress distributions are found to be in good agreement with previous results, supporting the contention that the shear stress distribution is essentially independent of Mach number and heat transfer for Mach numbers from incompressible to hypersonic and wall to freestream temperature ratios of 0.4 to 1.0. It is also found that corrections for frequency response limitations of the electronic equipment are necessary to determine the correct shear stress distribution, particularly at the walls.
 Publication:

AIAA Journal
 Pub Date:
 July 1979
 DOI:
 10.2514/3.61211
 Bibcode:
 1979AIAAJ..17..736L
 Keywords:

 Compressible Boundary Layer;
 Shear Flow;
 Shear Layers;
 Shear Stress;
 Turbulent Boundary Layer;
 Aerothermodynamics;
 Flat Plates;
 Flow Velocity;
 Free Jets;
 HotWire Anemometers;
 Mach Number;
 Stress Distribution;
 Stress Measurement;
 Two Dimensional Bodies;
 Fluid Mechanics and Heat Transfer