Computation of steady and unsteady control surface loads in transonic flow

A computational procedure for the analysis of loads due to steady and oscillatory control surface deflections is presented. Viscous effects, including mild separation, are modeled using an interactive boundary layer and the transpiration velocity approach. Numerical results are presented for a three-dimensional transport aircraft wing with supercritical sections, for control surfaces located at the trailing edge and the leading edge, for steady as well as oscillatory deflections. Results are compared with experimental data as well as with linear theory.