Modeling a supersonic flowfield in the core of the wingtip vortex at Mach 6

In this paper numerical calculations of a wingtip vortex for various wing angles of attack are presented, and the resulting flow modes are compared with each other and with the experimental data. Numerical computations were performed at the Keldysh Institute of Applied Mathematics, making use of the Spalart-Allmaras turbulence model. Experiments were carried out at the Institute of Theoretical and Applied Mechanics, Siberian Branch (SB), Russian Academy of Sciences (RAS), Khristianovich, Russia.