NUMERICAL FLOWFIELD ANALYSIS OF THE NEXT-GENERATION VULCAN NOZZLE

For numerical simulations of reacting, viscous nozzle flows in advance d rocket nozzles, a numerical method has been developed. The code is b ased on the well established DLR Euler/thin layer Navier-Stokes code N SHYP that was originally written for hypersonic re entry how simulatio ns. The code solves the three-dimensional, time-dependent Euler and th in-layer Navier-Stokes equations in conservation law form, Hydrogen an d oxygen are considered as fuel and oxidizer, respectively. The passiv e scaler approach accounts for the multicomponent diffusion effects. T urbulent transport is described with an algebraic eddy-viscosity, and a k-epsilon two-equations model. Calculations of conventional bell noz zles were performed, Results of Vulcan Mark 1 nozzle flow simulations are shown and compared in detail with another well-established numeric al approach, based an the method of characteristics. A modified Vulcan engine is proposed, where the gas generator exhaust gases are injecte d into the main nozzle. Results of an engine analysis are presented. B ased on this engine analysis, numerical flowfield calculations of the modified nozzle were performed and are presented.