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https://doi.org/10.1017/s0001924000054403
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Cite Publication Date: Oct 1, 1967 | |
 Citations: 3 |
Affiliation: University of Liverpool
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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