Abstract:

A potential difference method for computing the aerodynamic loads on wings in fully unsteady, subsonic, high angles of attack flows with leading-edge or side-edge separations is presented in this paper. For this type of nonlinear problems, the developed method can provide the time varying aerodynamic loads and the velocity fields in time domains. The numer;cal results show in good agreement with the experimental data.

Key words: subsonic, high angle of attack, unsteady, nonlinear aerodynamic