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):

Report Date:

1967-08-31

Pagination or Media Count:

83.0

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 ms. 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

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics
  • Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE