J. Wallisch, R. Hann

Atmospheric icing is a key challenge of the operational envelope of unmanned aerial vehicles. Especially medium-sized fixed-wing UAVs suffer from the consequences of ice accretions. Icing wind tunnels are important facilities to do experiments and gain more insight into atmospheric icing. However, the number of suitable icing wind tunnels for UAVs is low. This work describes the design of a possible icing wind tunnel specifically designed for UAV applications. The icing wind tunnel design is of the open-return type and has a dimension of 8 m x 1.5 m x 1.5 m. With the possibility to test median volume diameters of maximum 40 ìm, the icing wind tunnel covers a wide range of in-cloud icing conditions. To ensure a steady run of the icing wind tunnel, a fan power of 8 kW is necessary as well as a cooling power of 20 kW. This work also contains the results of flow simulations of the icing wind tunnel. These CFD results show flow separation which needs to be taken into consideration for the next design steps.

Deutscher Luft- und Raumfahrtkongress 2020

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2020

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

urn:nbn:de:101:1-2020091413310850172146

10.25967/530188

UAVs, Icing Wind Tunnel

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Wallisch, J.; Hann, R. (2020): Design of a Low-Speed Icing Wind Tunnel for UAVs. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/530188. urn:nbn:de:101:1-2020091413310850172146.

14.09.2020