Volume 2, 2011Progress in Propulsion Physics
|Page(s)||675 - 692|
|Published online||01 October 2012|
Optimization of supersonic axisymmetric nozzles with a center body for aerospace propulsion
ICARE − Institut de Combustion Aérothermique, Réactivité et Environnement, CNRS Av. de la Recherche Scientifique 1C, Orléans 45071, France
2 MBDA France Av. Réaumur 1, Le Plessis Robinson 92358, France
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 2nd and 3rd 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 to 0.4 m. For these contours, Navier-Stokes (NS) simulations have been performed to take into account viscous effects assuming adiabatic and cooled wall conditions. The paper presents an analysis of factors influencing the nozzle thrust.
© Owned by the authors, published by EDP Sciences, 2011