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A Stagnation Pressure Probe for Supersonic and Subsonic Flows

Published online by Cambridge University Press:  07 June 2016

M J Goodyer
M J Goodyer*
Affiliation:
The University, Southampton
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Summary

The usefulness of a probe which can sense the absolute value of the stagnation pressure in supersonic flow has long been recognised. In the past such a probe has not been available and therefore it has been necessary to infer this fundamentally important flow property from measurements of other properties. This paper describes a probe which has been developed specifically to measure accurately the stagnation pressure of a supersonic gas stream. Measurements of the performance of the probe to date show that it is capable of measuring absolute stagnation pressure with an accuracy of 0.1 per cent in the Mach number range 1.5 to 2.1. No measurements have yet been made in the transonic range, but at low subsonic speeds the probe has demonstrated its ability to measure dynamic pressure within an accuracy of 0.1 per cent at a Mach number of approximately 0.13. The permissible range of misalignment in pitch and yaw before the pressure recovery begins to deteriorate are functions of free-stream Mach number and are usefully wide.

Type
Research Article
Information
Aeronautical Quarterly , Volume 25 , Issue 2 , May 1974 , pp. 91 - 100
Copyright
Copyright © Royal Aeronautical Society. 1974

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References

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