WALL TEMPERATURE EFFECTS ON SUBSONIC GAS FLOW.
CATHOLIC UNIV OF AMERICA WASHINGTON D C DEPT OF MECHANICAL ENGINEERING
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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
- Fluid Mechanics