USING A HIGH-RESOLUTION SCHEME IN A FINITE VOLUME CODE TO SIMULATE SUPERSONIC COMPRESSIBLE FLUID FLOWS IN NOZZLES

Abstract

In this work, numerical simulations were carried out for supersonic compressible fluid flows inside geometries related to rocket engines — specifically, convergent-divergent nozzles. To investigate the flow behavior within these nozzles, the Euler and Navier–Stokes equations were numerically solved. The simulations were performed using the HYNE2D code, which is based on the finite volume method and implemented in the Fortran 2003 programming language. The HYNE2D code includes numerous convective and viscous flux functions and performs time discretization either explicitly or implicitly on unstructured meshes. The simulations based on the Euler equations aimed to verify the numerical accuracy of the code through the physical consistency of the results. For the Navier–Stokes equations, the objective was to assess whether the high-resolution method accurately captures shock and expansion waves while reproducing a Mach number equal to one at the nozzle throat. Additionally, the study analyzed the conversion of thermal energy into kinetic energy in bell-shaped and conical nozzles. The results obtained in this work were compared with related literature, showing good accuracy.

DOI: https://doi.org/10.56238/edimpacto2025.086-003