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

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-thickn...

Full description

Saved in:
Bibliographic Details
Published in:Journal of fluid mechanics 1973-09, Vol.60 (2), p.257-271
Main Authors: Coleman, G. T., Osborne, C., Stollery, J. L.
Format: Article
Language:English
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary: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.
ISSN:0022-1120
1469-7645
DOI:10.1017/S0022112073000157