Abstract
A simple approximative method for design of the transonic region of rapid expansion nozzles is described for two-dimensional plane case using elements of the exact solution of the transonic potential equation for nozzles with continuous contours of slender body type. The results are in satisfactory correspondence with known experiments and values gained by the hodograph method. The features of the flow near the nozzle edge such as the bellied downstream form of the sonic line and the succession of other dominating lines are discussed as well as the special conditions for establishing a method of characteristics for the calculation of the supersonic nozzle region.
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