The aerodynamic load characteristics and the performance degradation of moderate aspect
ratio wings with simulated glaze leading-edge ice have been studied using a three-dimensional compressible
Navier-Stokes solver. Correlation of predictions with experimental data for swept wings with and without
leading-edge ice formation shows the ability of the present computational technique to predict accurately
both the distributed surface pressures and integrated sectional loads. The leading-edge flow separation
and reattachment on the wing surface caused by the leading-edge ice shape are also well captured, showing
a vortex formation and the spanwise migration of the flow inside the separated flow region. The
performance degradation of the wing as a result of the leading-edge ice formation is numerically well
demonstrated.