Abstract
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.
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