Abstract
Uniform plane supersonic flow and rotational flow around a cylinder are connected on several points of the symmetrical curved shock, satisfying shock conditions. The analysis consists of two processes. First, the stream function of the flow pattern behind the shock is expressed in some trigonometric series with undetermined coefficients. Then, assuming the shape and the location of the shock wave, linear equations of these coefficients are introduced by shock conditions.The particular example of free-stream Mach number 2 around a circular cylinder has been worked out with a three-parameter approximation and the density variation along the axis is compared with data obtained by an experiments. Improvements and extentions of this parametric method are briefly given in the last section.
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