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
      Fluid Mechanics
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE