Accession Number:

ADA046365

Title:

Investigation of the Structure of a Cooled Wall Turbulent Supersonic Boundary Layer.

Descriptive Note:

Final rept. 24 Mar 75-23 Jul 77,

Corporate Author:

FORD AEROSPACE AND COMMUNICATIONS CORP NEWPORT BEACH CALIF AERONUTRONIC DIV

Personal Author(s):

Report Date:

1977-10-01

Pagination or Media Count:

135.0

Abstract:

This report presents mean flow profiles across a two-dimensional, flat plate, compressible turbulent boundary layer. The mean flow properties were determined from pitot pressure and total temperature surveys carried out at three streamwise locations for wall to freestream total temperature ratios of 0.94 adiabatic case, 0.714 and 0.54. All tests were conducted for a freestream Mach number of 3.0 with Reynolds number, based on momentum thickness, varying from 3200 to 4200. Although the outer two thirds of the viscous sublayer was probed, no evidence was found of a linear velocity gradient near the wall. However, the skin friction calculated using two conventional correlations were in good agreement with the trend of data. Furthermore, comparison of the velocity profile with Coles Law-of-the-Wake correlation indicated that the boundary is characteristic of a fully developed zero pressure gradient, flat plate flow. Results were in accord with those of other investigators for supersonic flows. In particular, the calculated eddy viscosity was in excellent agreement with the correlation derived by Maise and McDonald.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE