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    Interaction between a normal shock wave and a turbulent boundary layer at high transonic speeds. Part 1: Pressure distribution (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical solutions are derived which incorporate additional physical effects as higher order terms for the case when the sonic line is very close to the wall. The functional form used for the undisturbed velocity profile is described to indicate how various parameters will be calculated for later comparison with experiment. The basic solutions for the pressure distribution are derived. Corrections are added for flow along a wall having longitudinal curvature and for flow in a circular pipe, and comparisons with available experimental data are shown.
    Keywords: AERODYNAMICS
    Type: NASA-CR-158541
    Format: application/pdf
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