ANALYSIS OF A WING-TIP-MOUNTED SMALL-SCALE PROPELLER CONFIGURATION UNDER NON-AXIAL INFLOW CONDITIONS

Cerny M.; Herzog N.; Breitsamter C.

Title:: ANALYSIS OF A WING-TIP-MOUNTED SMALL-SCALE PROPELLER CONFIGURATION UNDER NON-AXIAL INFLOW CONDITIONS
Document type:: Konferenzbeitrag
Contribution type:: Textbeitrag / Aufsatz
Author(s):: Cerny M.; Herzog N.; Breitsamter C.
Abstract:: Regarding the design of the propeller propulsion system of small and medium-sized aircraft and UAVs there is still a need for an aerodynamic analysis of the specific flow characteristics of such vehicles, namely, the combination of small propeller dimensions and a wide range of inflow angles. In this work, a wing-tip-mounted propeller is analyzed both experimentally as well as by URANS calculations. Analyzed are the behavior of time-averaged aerodynamic reaction forces regarding thrust, lift, and pitching moment, the surface pressure along the wing contour, and the occurring flow field. © 2021 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021. All rights reserved. «
Regarding the design of the propeller propulsion system of small and medium-sized aircraft and UAVs there is still a need for an aerodynamic analysis of the specific flow characteristics of such vehicles, namely, the combination of small propeller dimensions and a wide range of inflow angles. In this work, a wing-tip-mounted propeller is analyzed both experimentally as well as by URANS calculations. Analyzed are the behavior of time-averaged aerodynamic reaction forces regarding thrust, lift, an... »
Keywords:: Drone; Propeller; UAV; URANS; Wind tunnel
Dewey Decimal Classification:: 620 Ingenieurwissenschaften
Book / Congress title:: International Council of the Aeronautical Sciences
Congress (additional information):: 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021, Shanghai, 6 September 2021 through 10 September 2021, Code 176566
Year:: 2022
Covered by:: Scopus
Print-ISBN:: 978-393218291-4
Language:: en
Notes:: Funding text: The authors would like to thank the Bavarian Research Foundation (Bayerische Forschungsstiftung) for funding the research project under the grant number AZ-1277-17. Further, we gratefully acknowledge the successful collaboration and support by the project partner Rolls-Royce Deutschland Ltd & Co KG. We give special thanks to ANSYS for providing the flow simulation software and the company APC Propellers for providing the geometrical data of the analyzed propeller.
TUM Institution:: Lehrstuhl für Aerodynamik und Strömungsmechanik
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