Simulation of a supersonic flowfield in the tip vortex core at Mach number of 6

In this work there are presented: numerical simulations of the wing-tip vortex for various attack angles of the wing, comparing the resulting flow regimes among themselves and with the experimental data. Numerical simulations were executed using the turbulence model of Spalart–Allmaras in the Keldysh Institute of Applied Mathematics RAS. Experiments were realized in Khristianovich Institute of Theoretical and Applied Mechanics SB RAS.