A cylindrical protuberance mounted on a flat plate will cause the plate boundary layer to separate if the cylinder is long compared to the boundary-layer height. Tests made at M = 4.9 using an oil-flow technique are employed to determine the upstream extent of cylinder influence on a turbulent boundary layer. The results are found to be in reasonable agreement with data from other investigators for a wide range of flow conditions. A method is given for determining the angle of the oblique shock wave caused by separation. This permits calculation of the location of the triple point of the lambda shock pattern that characterizes the flow. An approximate method of calculating the peak value of the cylinder stagnation pressure and the location of the peak is also presented.
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J. C. Westkaemper (1968) studied this question.
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