Contouring two-sided asymmetric plane maximum-thrust nozzles

The results of the optimal contouring of asymmetric plane nozzles under some additional constraints are presented. One of the constraints is due to the asymmetric arrangement of the unknown nozzles relative to the combustion chamber exit. The investigation is based on the numerical integration of the Reynolds-averaged Navier–Stokes equations and direct optimization methods using genetic algorithms and the representation of the optimized contours in the form of the Bernstein–Bézier curves.