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

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 §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 to take into account viscous e¨ects assuming adiabatic and cooled wall conditions. The paper presents an analysis of factors in §uencing the nozzle thrust.

Pressure Distribution and Performance Impacts of Aerospike Nozzles on Rotating Detonation Engines

“…The nozzle contour must be carefully optimized to provide the maximum thrust for given geometric limitations [39]. An ideally contoured nozzle produces a uniform, one-dimensional flow profile in the exit plane [40].…”

“…Many design approaches have been investigated, including those based on the Method of Characteristics (MOC) [42], [43], [44], Rao's calculus of variations [13], a simple approximate method [45], [22], or some combination of these methods. In fact, many aerospike nozzle designs simply use some combination of quadratic functions [41], 2nd or 3rd order polynomials [39], [46], circular arcs, and/or parabolas [30] to describe the contour. Onofri et al [21] provide an extensive summary of plug nozzle contour design methods.…”