Steady and unsteady transonic airloads on a supercritical wing

A brief description of an experimental investigation to determine steady and unsteady airloads on a fixed and an oscillating supercritical wing model is presented. Steady and unsteady data are correlated with results of computational methods for various representative cases. Steady transonic flow computations were carried out using the XTRAN3S code and the Bailey-Ballhaus/McNally code. Unsteady flow computations were performed using the XTRAN3S code and a quasi-three-dimensional method, which combines the LTRAN2-NLR code with subsonic theory. Compared to the experimental data, the computed results show qualitatively similar transonic effects on pressure distributions and lift coefficients. The accuracy, however, is only modest.