An analytic method is presented for determining the contours of two-dimensional supersonic nozzles having continuous curvature. The continuity of curvature is necessary for flexible-plate type nozzles inasmuch as the aerodynamic contour must be such that it can be closely simulated by the elastic curve of the flexible plate. The method described is more accurate and less time consuming than the characteristics method of obtaining contours. The assumption is made that radial flow can be obtained at the inflection point through the use of a simple polynomial for the initial part of the contour. This radial flow is converted to parallel flow at the test section Mach number as described herein.
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