Open AccessNovell Application of CFD for Rocket Engine Nozzle Optimization
Author(s) -
Csaba Jéger,
Árpád Veress
Publication year - 2018
Publication title -
periodica polytechnica. transportation engineering
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.388
H-Index - 15
eISSN - 1587-3811
pISSN - 0303-7800
DOI - 10.3311/pptr.11490
Subject(s) - nozzle , multiphysics , computational fluid dynamics , thrust , conical surface , rocket engine nozzle , parametric statistics , computer science , mechanical engineering , discharge coefficient , simulation , mechanics , engineering , aerospace engineering , finite element method , structural engineering , mathematics , physics , statistics
Numerical analyses, validation and geometric optimization of a converging-diverging nozzle flows has been established in the present work. The optimal nozzle contour for a given nozzle pressure ratio and length yields the largest obtainable thrust for the conditions and thus minimises the losses. Application of such methods reduces the entry cost to the market, promote innovation and accelerate the development processes. A parametric geometry, numerical mesh and simulation model is constructed first to solve the problem. The simulation model is then validated by using experimental and computational data. The optimizations are completed for conical and bell shaped nozzles also to find the suitable nozzle geometries for the given conditions. Results are in good agreement with existing nozzle flow fields. The optimization loop described and implemented here can be used in the all similar situations and can be the basis of an improved nozzle geometry optimization procedure by means of using a multiphysics system to generate the final model with reduced number sampling phases.