Accession Number : AD0699133
Title : AN EXPERIMENTAL INVESTIGATION OF THE COMPRESSIBLE TURBULENT BOUNDARY LAYER WITH A FAVORABLE PRESSURE GRADIENT.
Descriptive Note : Final rept.,
Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD
Personal Author(s) : Brott,David L. ; Yanta,William J. ; Voisinet,Robert L. ; Lee,Roland E.
Report Date : 25 AUG 1969
Pagination or Media Count : 80
Abstract : The paper describes the results of a detailed experimental investigation of a two-dimensional turbulent boundary layer in a favorable pressure gradient where the free-stream Mach number varied from 3.8 to 4.6 and the ratio of wall to adiabatic-wall temperature has a nominal value of 0.82. Detailed profile measurements were made with pressure and temperature probes; skin friction was measured directly with a shear balance. The velocity- and temperature-profile results were compared with zero pressure gradient and incompressible results. The skin-friction data were correlated with momentum-thickness Reynolds number and pressure-gradient parameter. (Author)
Descriptors : (*TURBULENT BOUNDARY LAYER, *TWO DIMENSIONAL FLOW), COMPRESSIBLE FLOW, PRESSURE, SUPERSONIC CHARACTERISTICS, SKIN FRICTION, MOMENTUM, REYNOLDS NUMBER
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE