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This study is aimed at optimization of axisymmetric nozzles with a center body, which are suitable for thrust engines having an annular duct. To determine the §ow conditions and nozzle dimensions, the Vinci rocket engine is chosen as a prototype. The nozzle contours are described by 2nd and 3rd order analytical functions and speci¦ed by a set of geometrical parameters. A direct optimization method is used to design maximum thrust nozzle contours. During optimization, the §ow of multispecies reactive gas is simulated by an Euler code. Several optimized contours have been obtained for the center body diameter ranging from 0.2 to 0.4 m. For these contours, Navier Stokes (NS) simulations have been performed

Optimization of supersonic axisymmetric nozzles with a center body for aerospace propulsion