Implementation of Flux Limiters in Simulation of External Aerodynamic Problems on Unstructured Meshes

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 that use second-order approximation reconstruction solution facet. A with shock wave structures considered, where, prevent oscillations at discontinuous solutions, order accuracy reduced due implementation function gradient. In particular, Venkatakrishnan was chosen. analyses this as it impacts results monotonicity solution. It shown that, used in classical formulation, operation threshold based characteristic size cell mesh, facilitates suppression non-physical upgrade its monotonicity. However, computing meshes, setup can result occurrence areas accidental activation, influences produced result. proposed where formulation gas dynamics parameters flow. option characterized by absence parasite regions activation ensures only region high gradients. Monotonicity properties, compared are preserved. Constants thresholds both options example numerical problem processes different Recommendations regarding optimum values these quantities provided. Problems supersonic channel wedge transonic over NACA0012 airfoil were selected examination functions applicability. computation carried out meshes consisting tetrahedrons, truncated hexahedrons, polyhedrons. such case modified function, implemented. analysis field around indicates improved enables an increase