Abstract:

Compressible flow around an NACA 0012 airfoil at high angle of attack is numerically simulated by solving the two-dimensional Navier-Stokes equations in a body-fitted system, the grid system is C-type grid generated algebraically. The LU-ADI algorithm is employed in this paper, in order to control the numerical stability, the second-order and fourth-order artificial dissipation are added to the basic algorithm. By using the Baldwin-Lomax turbulent model, the formation of the leading edge separation bubble, as well as the convection of vortex along the airfoil surface and unsteady phenomena of vortex are simulated at high angle of attack. For some Mach numbers and angles of attack, the NACA 0012 airfoil turbulent solutions are periodie. By the comparison, the results in this paper agree with experiments and results received by other method.

Key words: high angle of attack aerodynamics, separated flow, unsteady flow