Heat transfer from a hypersonic turbulent boundary layer on a flat plate-Reference-Cited by-同舟云学术

Heat transfer from a hypersonic turbulent boundary layer on a flat plate

Published:1973-09-04 Issue:2 Volume:60 Page:257-271
ISSN:0022-1120
Container-title:Journal of Fluid Mechanics
language:en
Short-container-title:J. Fluid Mech.

Author:

Coleman G. T.,Osborne C.,Stollery J. L.

Abstract

A hypersonic gun tunnel has been used to measure the heat transfer to a sharpedged flat plate inclined at various incidences to generate local Mach numbers from 3 to 9. The measurements have been compared with a number of theoretical estimates by plotting the Stanton number against the energy-thickness Reynolds number. The prediction giving the most reasonable agreement throughout the above Mach number range is that due to Fernholz (1971).The values of the skin-friction coefficient derived from velocity profiles and Preston tube data are also given.

Publisher

Cambridge University Press (CUP)

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics

Reference17 articles.

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