In the present article, in-flight ice formation on finite wings and air intakes of low-speed aircraft are numerically studied. The approach to the problem involves calculation of the velocity field using a three-dimensional panel method. Using the calculated velocity field, the droplet trajectories and droplet impact locations are computed yielding the droplet collection efficiency distribution. In the next step, convective heat transfer coefficient distributions around the geometries are calculated using a two-dimensional Integral Boundary-Layer Method, which takes surface roughness due to ice accretion into account. A thermodynamic analysis employing the Extended Messinger Method yields the ice growth rates. Integration of these rates over time yields the ice shapes, hence the modified geometry. Predicted ice shapes are compared with experimental shapes reported in the literature and good agreement is observed. Ice shapes around vastly varying geometries including complex shapes are successfully computed. As such, the developed tool may be used for academical purposes or for airworthiness certification efforts.