Accession Number : AD0746662

Title :   Temperature Distributions in Supersonic Turbulent Boundary Layers,

Corporate Author : AERODYNAMISCHE VERSUCHSANSTALT GOETTINGEN (WEST GERMANY)

Personal Author(s) : Meier,H. U. ; Rotta,J. C.

Report Date : 16 MAR 1971

Pagination or Media Count : 9

Abstract : Experimental investigations of total temperature and Mach number distributions in turbulent boundary layers have been performed in the Mach number range from 1.75 to 4.5, using a newly developed combined temperature and pressure probe. The measurements carried out so far have been used to reanalyze the process of heat transport by calculating the turbulent Prandtl number distribution throughout the boundary layer. The results show an increase of the turbulent Prandtl number close to the surface, thus indicating that the turbulent transport of heat decreases more rapidly towards the wall than the turbulent transport of momentum. A simple relation, based on the Prndtl mixing length theory, is proposed for the variation of the turbulent Prandtl number within the viscous layer. This relation gives temperature distributions that are in good agreement with the experimental data in the region of constant shear stress. (Author)

Descriptors :   (*TURBULENT BOUNDARY LAYER, TEMPERATURE), (*SUPERSONIC FLOW, TURBULENT BOUNDARY LAYER), STATISTICAL DISTRIBUTIONS, WIND TUNNEL MODELS, PROBES, SKIN FRICTION, HEAT TRANSFER, EQUATIONS OF MOTION, PRANDTL NUMBER, FLAT PLATE MODELS, NOZZLE THROATS, WEST GERMANY

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE