Abstract
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 flow conditions and nozzle dimensions, the Vinci rocket engine is chosen as a prototype. The nozzle contours are described by 2 nd and 3 rd order analytical functions and specified by a set of geometrical parameters. A direct optimization method is used to design maximum thrust nozzle contours. During optimization, the flow 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 m to 0.4 m and the nozzle length from 2.6 m to 3.4 m. For this contours, NavierStokes simulations have been performed to take into account viscous effects assuming adiabatic and cooled wall conditions. The effect of the center body truncation is examined. The factors influencing the nozzle thrust are analyzed. Nomenclature
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