Research on the hysteresis properties of unsteady aerodynamics about the oscillating wings

In the work, it is shown the numerical investigations about the unsteady inviscid results obtained for the pitching oscillating wings at different angles of attack. The results are obtained by solving the unsteady Euler equations in a body-fitted coordinate system. It is based on the four-stage Runge-Kutta time stepping scheme. Meanwhile to increase the time step that is limited by Courant limit (CFL), the implicit residual smoothing with local variable parameters is used. As a result, the unsteady aerodynamics about a rectangular wing and a delta wing, which are oscillated in pitching with different frequencies, are shown in this paper. The properties of the unsteady aerodynamics in these cases are researched here.