Numerical Investigation of the Vortex Roll-up from a Helicopter Blade Tip using a Novel Fixed-wing Adaptation Method

This contribution relates to the simulation of the flow around the tip of a helicopter rotor blade in hovering flight conditions. We here propose a new methodology of framework adaptation, using a comprehensive rotor code and high-fidelity numerical simulations. We construct an equivalent fixed-wing configuration from a rotating blade, in which centrifugal and Coriolis forces are neglected. The effect of this approximation on the solution is analyzed. The method is validated by a detailed comparison with wind tunnel data from the literature, concerning aerodynamic properties and tip vortex roll-up. This validation also includes variations of the pitch angle and rotational speed, up to transonic tip velocities. Compared to previously published methods of framework adaptation, the new hybrid method is found to reproduce more accurately the flow around a rotating-blade tip.

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    • Copyright © 2017, Deutsches Zentrum für Luft- und Raumfahrt e.V. The contents of this paper reflect the views of the author[s] and do not necessarily reflect the official views or policies of the Transportation Research Board or the National Academy of Sciences.
  • Authors:
    • Joulain, Antoine
    • Desvigne, Damien
    • Alfano, David
    • Leweke, Thomas
  • Publication Date: 2017-6

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  • English

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  • Accession Number: 01636364
  • Record Type: Publication
  • Files: TRIS
  • Created Date: May 15 2017 9:13AM