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Temperature measurements in a hypersonic gun tunnel using heat-transfer methods

Published online by Cambridge University Press:  28 March 2006

B. E. Edney
B. E. Edney
Affiliation:
The Aeronautical Research Institute of Sweden (FFA)
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Abstract

The theory of Fay & Riddell (1958) is used to calculate stagnation temperatures from stagnation-point heat-transfer rates measured in the working section of a hypersonic gun tunnel at a Mach number of 9·8. Measurements using both thin-film gauges and calorimeters are described. The temperatures measured using this technique are found to be lower than predicted by Lemcke (1962) from measurements of shock strengths and final pressures in the gun barrel. This discrepancy is attributed to heat losses in the barrel during the initial shock compression cycle. A simple theory is developed to take into account these losses. There is good agreement between this theory and the experimental results.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 27 , Issue 3 , 24 February 1967 , pp. 503 - 512
Copyright
© 1967 Cambridge University Press

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References

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