Icing formation on aircraft can degrade aerodynamic performance and control. Experimental campaigns have been conducted to better understand the phenomenon. Usually, computational icing methods represent a valid aid to relax the costs of experimental measurements especially at the early design stages. However, the irregular shape of accreted ice makes the mesh generation process challenging for both structured and unstructured methods. This motivates the idea of a numerical study aiming to evaluate whether numerically generated, smoother growth can effectively replace the irregular shape of experimentally measured ice when estimating aerodynamic losses. If robust and enough accurate, such an approach would allow to relax geometric details and reduce the meshing effort, especially when adopting body-conformal strategies. This work discusses the aerodynamic degradation calculations of two iced cases with IBM method usign in-house CIRA code SIMBA. Overall, the main objective of the present study is assessing the viability of employing numerically generated ice geometries as substitutes for complex experimental configurations in the estimation of aerodynamic losses. Potentially, this strategy could represent an alternative to the body-conformal meshing of intricate three-dimensional ice formations offering a substantial reduction in grid resolution requirements when utilizing automated Cartesian or IBM based strategies