CFD Investigation of Asymmetric Three-Dimensional Supersonic Nozzle MLN for Rocket Engine
DOI:
https://doi.org/10.3849/aimt.02007Keywords:
CFD, supersonic nozzle, streamline, Ansys-Fluent software, Method of Characteristics, high temperature model, minimum length nozzleAbstract
This study focuses on the design of asymmetric supersonic nozzles to improve the performance of conventional axisymmetric propulsion systems. A numerical calculation program based on the Method of Characteristics (MOC) at high temperature was developed to design three-dimensional nozzles with arbitrary exit sections. The streamlines are obtained by integrating the axisymmetric flow function, and the three-dimensional geometry is generated by tracing the exit section parameters back to the throat. Five nozzle shapes were investigated: square, circular, hexagonal, rectangular, and elliptical. CFD simulations using Ansys-Fluent were performed to validate the designs for an exit Mach number of 4.00 with air as the working fluid. The results show very good agreement with the Fortran program calculations, confirming its accuracy and highlighting the influence of exit geometry on nozzle performance.
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