Hostname: page-component-78c5997874-j824f Total loading time: 0 Render date: 2024-11-03T01:27:30.607Z Has data issue: false hasContentIssue false
  • English
  • Français

The response of a pitot tube in the presence of a weak shock wave

Published online by Cambridge University Press:  04 July 2016

G. T. Kalghatgi  and
B. L. Hunt
G. T. Kalghatgi
Affiliation:
Department of Aeronautical Engineering, University of Bristol
B. L. Hunt
Affiliation:
Department of Aeronautical Engineering, University of Bristol
Get access Rights & Permissions [Opens in a new window]

Extract

This note is concerned with the response of a pitot tube in the region of its interaction with a weak shock wave. It will be helpful if we distinguish immediately between our usage of the terms ‘pitot pressure’ and ‘normal shock recovery pressure’. We use the former to mean the experimental reading obtained from a pitot tube and the latter to mean the theoretical stagnation pressure downstream of a normal shock at the Mach number of a point in the flow.

Across an oblique shock, the normal shock recovery pressure changes discontinuously. However, in the course of a recent study of the impingement of supersonic jets on flat plates, the authors noticed that, as a pitot probe was traversed across a weak shock wave, not only was the discontinuity smoothed out by the finite size of the probe but also values of pitot pressure were obtained which were larger than the higher of the two values of normal shock recovery pressure.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 80 , Issue 784 , April 1976 , pp. 183 - 185
Copyright
Copyright © Royal Aeronautical Society 1976 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

Now Department of Aeronautics and Astronautics, University of Southampton.

References

1. Kalghatgi, G. T. Some aspects of supersonic jet impingement on plane perpendicular surfaces. University of Bristol. PhD Thesis. 1975.Google Scholar
2. Gummer, J. H. and Hunt, B. L. The impingement of a uniform, axisymmetric, supersonic jet on a perpendicular flat plate. The Aeronautical Quarterly, Vol 22, No 4, pp 403–420, 1971.Google Scholar
3. Carling, J. C. The impingement of uniform axisymmetric supersonic jets of air on plane perpendicular surfaces. University of Bristol, PhD Thesis. 1974.Google Scholar
4. Henderson, L. F. On the confluence of three s'mck waves in a perfect gas. The Aeronautical Quarterly, Vol 15, No 2, pp 181–197, 1964.Google Scholar
5. Henderson, L. F. The three-shock confluence on a simple wedge intake. The Aeronautical Quarterly, Vol 16, No 1, pp 42–53. 1965.Google Scholar
6. Kalghatgi, G. T. and Hunt, B. L. The three-shock confluence problem for normally impinging, over-expanded jets The Aeronautical Quarterly, Vol 26, No 2, pp 117– 132, 1975.Google Scholar