Numerical simulation of a vortex wake behind a wing at a wide distance from the wing in supersonic flow
In this paper we present a wingtip vortex numerical study in the supersonic regime at a wide distance from the wing with the Mach number M=3. The wing incidence is 10°. Reynolds`s averaged Navier-Stokes equations with the Spalart-Allmaras turbulence model were used to describe the flow. Numerical simulations were made in Keldysh Institute of Applied Mathematics Russian Academy of Sciences. A parallel implementation of algorithms for simulating turbulent flows on multiprocessor computer systems was used.
wingtip vortex, supersonic flow, numerical simulation, URANS, LES
Publication language:russian, pages:15
Mathematical modelling in actual problems of science and technics