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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
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.
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- Copyright © Royal Aeronautical Society 1967
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