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Validation of a Flow Simulation for a Helicopter Fuselage Including a Rotating Rotor Head

  • Moritz Grawunder
  • Roman Reß
  • Victor Stein
  • Christian Breitsamter
  • Nikolaus A. Adams
Conference paper
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume 132)

Abstract

This work presents a detailed analysis of the aerodynamic characteristics for a helicopter fuselage including a skid-landing-gear and a rotating rotor head. Thereby, a special emphasis is set on the rotor head. The results are obtained through numerical simulations based on the incompressible URANS equations. The modelling of the rotating rotor head, including collective and cyclic pitch, is based on a sliding mesh interface in combination with mesh deformation. The numerical simulations are performed under the same conditions and at the same scale as for the existing wind tunnel data. Thus a detailed validation study based on the broad experimental data base could be performed. For this purpose the experimental data base was further extended by rotor phase locked stereo particle image velocimetry measurements.

Keywords

Rotor aerodynamics Cyclic Sliding mesh Mesh deformation 

Notes

Acknowledgments

The research leading to these results received funding from the European Community’s Seventh Framework Program (FP/2007-2013) for the Clean Sky Joint Technology Initiative under grant agreement number 270563. The authors would like to thank the project leader Eurocopter Deutschland GmbH for the fruitful collaboration and valuable support. Furthermore, special thanks are addressed to ANSYS CFX for providing the flow simulation software.

References

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Copyright information

© Springer International Publishing Switzerland 2016

Authors and Affiliations

  • Moritz Grawunder
    • 1
  • Roman Reß
    • 1
  • Victor Stein
    • 1
  • Christian Breitsamter
    • 1
  • Nikolaus A. Adams
    • 1
  1. 1.Lehrstuhl für Aerodynamik und StrömungsmechanikTechnische Universität MünchenGarching bei MünchenGermany

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