Design of axisymmetric supersonic/hypersonic nozzles

A method is given here for the design of axisymmetric13; supersonic/hypersonic nozzles. The final nozzle contour is13; obtained by adding the boundary-layer displacement to the inviscid contour. Method of characteristics is used in obtaining the inviscid contour. The initial data required to start the scheme of method of characteristics is in the form of Mach number distribution along the nozzle axis. Certain improvements are made to the unified approach of Sivells for obtaining a consistent and smooth distribution of Mach number along the nozzle axis. Equations are derived for calculating the mass flow across a characteristic between two field points. As a result of these relations it has been possible to locate the wall-streamline more accurately in the numerical work than by the previously existing methods