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%0 Thesis %A Hofmann, Jan-Philipp %T Gondelauslegung für Mantelpropellerantriebe %I Rheinisch-Westfälische Technische Hochschule Aachen %V Dissertation %C Aachen %M RWTH-2025-06777 %P 1 Online-Ressource : Illustrationen %D 2025 %Z Veröffentlicht auf dem Publikationsserver der RWTH Aachen University %Z Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2025 %X A design and evaluation method for the aerodynamic nacelle design of ducted fans is presented in this thesis. Based on an exemplary nacelle design for an ultralight aircraft powered by two electric ducted fan propulsion systems, the method is demonstrated and validated by experimental investigations under different inflow conditions on a prototype. Finally, important correlations for the aerodynamic nacelle design are presented. The design and evaluation method for the aerodynamic nacelle design is based on a design procedure for ducted fan propulsion systems which was developed at the Institute of Jet Propulsion and Turbomachinery. Different nacelle geometries are investigated for various operating points using numerical solutions of the Reynolds-averaged Navier-Stokes equations. For this purpose, the blading is represented by an actuator disk model which is set up uniquely for the blading and takes into account the local inflow velocity and the angle of attack. The operating performance and other parameters such as the total inlet pressure loss are evaluated. The method is validated by experimental studies on a reference geometry. Under axial flow conditions, the thrust increases with increasing power and decreases at higher flow velocity. The numerically calculated thrust values are, as expected, slightly higher than the measured data, and the calculated stagnation point positions correspond with the experimentally determined ones over the entire operating range. For increasing angle of attack, the calcultated thrust values enhance at constant flow velocity and constant propulsion power. This is confirmed by the experimental data, but at large angles of attack of about 40° the measured thrust is up to 10 %F PUB:(DE-HGF)11 %9 Dissertation / PhD Thesis %R 10.18154/RWTH-2025-06777 %U https://publications.rwth-aachen.de/record/1016159