NAVIER-STOKES COMPUTATIONS FOR OSCILLATING CONTROL SURFACES

Unsteady Navier-Stokes computations have been performed for simulating transonic flows over wings with oscillating control surfaces using a locally moving grid and a stationary-mismatched zoning scheme. An F-5 wing and a clipped delta wing are chosen for the present study. The co mputed unsteady pressures and the response characteristics to the cont rol surface motions are compared with experimental data. The results s uccessfully predict main features of the unsteady pressure profiles, s uch as the double peaks at the shock wave and at the hinge line.