ЧИСЛЕННОЕ МОДЕЛИРОВАНИЕ АВТОКОЛЕБАНИЙ ТРАНСЗВУКОВЫХ ТУРБУЛЕНТНЫХ ПОТОКОВ ПРИ ОБТЕКАНИИ АЭРОДИНАМИЧЕСКИХ ПРОФИЛЕЙ
Unsteady Reynolds-averaged Navier–Stokes equations along with the Spalart–Allmaras one-parameter differential turbulence model are applied to investigate the transonic flow over BGK No.1, OAT15A, NACA 0012 airfoils. The pressure and friction coefficient distributions on the airfoil surface, Mach number contour lines, numerical schlieren photographs, as well as the values of the aerodynamic coefficients are presented. The physical features of the shock wave–turbulent boundary layer interaction for the single-shock and double-shock self-oscillation regimes on the NACA 0012 airfoil were considered. An updated map of the transonic turbulent flow regimes around the NACA 0012 airfoil on the plane free-stream Mach number angle of attack is composed.
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