Accession Number : AD0661335
Title : WALL TEMPERATURE EFFECTS ON SUBSONIC GAS FLOW.
Descriptive Note : Final rept.,
Corporate Author : CATHOLIC UNIV OF AMERICA WASHINGTON D C DEPT OF MECHANICAL ENGINEERING
Personal Author(s) : Kelnhofer,Wm. J.
Report Date : 31 AUG 1967
Pagination or Media Count : 83
Abstract : A theoretical study is made for calculating various boundary layer thicknesses at a point on a heated or cooled wall assuming n-power velocity and m-power temperature profiles in subsonic gas flow. Also, boundary layer measurements are made for air flowing over a flat plate heated to 250C with velocities up to 30 m/s. The experimental results are compared to previous theoretical results assuming n = m and the velocity and thermal boundary layer thicknesses equal in fully developed flow. (Author)
Descriptors : (*SUBSONIC FLOW, *THERMODYNAMICS), (*BOUNDARY LAYER, THICKNESS), WALLS, TEMPERATURE, FLAT PLATE MODELS, TURBULENT BOUNDARY LAYER
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE