The present work introduces a modified scheme for the solution of compressible 2-D full Navier-Stokes equations, using Flux Vector Splitting method. As a result of this modification, numerical diffusion is reduced. The computer code which is developed based on this algorithm can be used easily and accurately to analyze complex flow fields with discontinuity in properties, in cases such as shock...

in this paper, by numerical simulation of gas flow, effects of divergence angles on the amplification factor, side force and thrust vector magnitude of a moveable nozzle with supersonic split line have been investigated. the study is conducted for constant exit to throat area ratio and the location of the split line is also constant. the finite volume method with second order upwind scheme for ...

A fully implicit solver is developed for the mesoscale nonhydrostatic simulation of atmospheric flows governed by the compressible Euler equations. To spatially discretize the Euler equations on a height-based terrain-following mesh, we apply a cell-centered finite volume scheme, in which an AUSM-up method with a piecewise linear reconstruction is employed to achieve secondorder accuracy for th...

The present work introduces a modified scheme for the solution of compressible 2-D full Navier-Stokes equations, using Flux Vector Splitting method. As a result of this modification, numerical diffusion is reduced. The computer code which is developed based on this algorithm can be used easily and accurately to analyze complex flow fields with discontinuity in properties, in cases such as shock...

A robust and efficient finite volume method with interface sharpening technique has been developed to solve the six-equation multi-fluid single-pressure model for compressible two-phase flows. The numerical is implemented in a three-dimensional vertex-centered code. least-squares reconstruction Kuzmin's vertex-based (VB) limiter fraction set of primitive variables presented framework. In region...

The study is dedicated to the peculiarities of implementing flux limiter flow quantity gradient when solving 3D aerodynamic problems using system Navier–Stokes equations on unstructured meshes. paper describes discretisation a finite-volume method and mathematical model including Spalart–Allmaras turbulence Advection Upstream Splitting Method (AUSM+) computational scheme for convective fluxes t...