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The Displacement of the Nose Shock Wave from a Pitot Tube under a Streamwise Velocity Gradient

Published online by Cambridge University Press:  04 July 2016

D. Sloan
D. Sloan*
Affiliation:
Fluid Mechanics Division, Dept of Mechanical Engineering, University of Liverpool
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Summary:—

The pressure reading of a pitot tube in a supersonic flow corresponds to the position of the nose shock wave. Results of measurements of the shock stand-off distance are presented for three different streamwise Mach number gradients and for a uniform flow. These results are compared with existing theoretical values.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 682 , October 1967 , pp. 725 - 726
Copyright
Copyright © Royal Aeronautical Society 1967

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References

1.Quincey, V. G. and Callinan, J.Experiments with a Pitot Rake at M=l.50. Journal of the Royal Aeronautical Society, Vol 67, No 636, p 793, December 1963.CrossRefGoogle Scholar
2.Moeckel, W. E. Approximate Methods for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies. NACA TN 1921, 1949.Google Scholar