Accession Number : ADA014730
Title : High Mach Number Turbulent Boundary Layer with and without Favorable Pressure Gradient.
Descriptive Note : Final rept. 1 Jun 72-1 Mar 75,
Corporate Author : NEW YORK UNIV WESTBURY AEROSPACE AND ENERGETICS LAB
Report Date : JUN 1975
Pagination or Media Count : 133
Abstract : Boundary layer profiles of total temperature and total pressure, together with surface pressure and heat transfer rates, in turbulent boundary layers with and without favorable pressure gradients have been measured with a Mach 6 wind tunnel facility. Experimental results were correlated and comparisons between the cases with and without favorable pressure gradient were made. Effects of pressure gradient and upstream history to the boundary layer development were investigated. Numerical results of an existing turbulent boundary layer theory were also compared with present experiments.
Descriptors : *Turbulent boundary layer, *Hypersonic characteristics, Transport properties, Hypersonic aircraft, Test facilities, Temperature, Pressure gradients, Test methods, Pressure, Measurement, Hypersonic wind tunnels, Numerical methods and procedures, Heat transfer, Enthalpy, Correlation techniques
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE