Unsteady N-S Calculations for NACA0012 Airfoil at High Angle of Attack Oscillating

Kurzfassung

The existing DLR code using the dual time method for solving the unsteady two-dimensional Navier-Stokes equations is improved to calculate the unsteady motion of NACA0012 airfoil oscillating at high angle of attack. Results obtained from single grid and multigrid calculations are given and compared with the experimental data. The influence of the magnitude of physical time step, the inner iteration tolerance, the artifical dissipative terms, the different farfield boundary treatments, the transition position and the correction smoothing coefficient, the cycle type and the number of levels in multigrid calculation is discussed in this report.