Constant increase of popularity of Unmanned Aerial Vehicles (UAVs) along with trend of withdrawal from use of combustion engines in favour of electric motors leads to emergence of new research fields in terms of human/goods transportation. In last years electric-powered drone-like small air vehicles became the subject of thorough research. Presented article focuses on numerical simulation of drone propeller, aiming at determination of CFD task setup. Subsequently, the model would be combined with Blade Element Theory approach into a hybrid simulation, allowing cost-efficient rotor optimization. The identification of critical flow structures (e.g. tip vortices, rotor wake helix) is essential for proper estimation of propeller performance in terms of thrust and generated power. Therefore, a proper choice of geometrical constraints, as well as boundary conditions, is subjected to study. Eventually, an important aspect is also the identification and minimization of noise sources – a simulation includes acoustics modelling. Two approaches for aerodynamically generated noise estimation are tested: Integral Method by Ffowcs Williams and Hawkings and Broadband Noise Source model. The study aims at defining a set of guidelines for propeller simulations, enabling the pre-assessment of rotor performance, flow structures and noise. In further steps, it would contribute to universal computational model for small aerial vehicles propellers optimization.

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