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Experiments of transonic flow past a circular arc profile show that the shock-wave pattern and the pressure distribution are strongly dependent upon the state of the boundary layer. A change from laminar to turbulent boundary layer at a given Mach Number changes the flow pattern considerably. waves can interact with the boundary layer in a manner similar to a reflection from a free jet boundary. These shock waves are not distinctly discernible from pressure distribution measurements.
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H. W. Liepmann (1946) studied this question.
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