Time and Frequency Domain Aerodynamics for Flutter of Helicopter Rotors in Hover

  • F. Mastroddi
  • L. Morino
Conference paper

Abstract

The objective of this work is to assess the accuracy of the aerodynamic modeling used in the flutter analysis of helicopter rotors in hover. A boundary-element formulation for unsteady potential incompressible flows is introduced. The results obtained for the aerodynamic forces, for pitch and flap, are compared with those typically used in the flutter analysis of rotors, (which are obtained using a strip-theory extension of Loewy’s formulation [3], although a boundary-element formulation has been used by Kwon [2] for a flutter analysis). The results demonstrate that Loewy’s formulation [3] yields results that are considerably different from those obtained with the more accurate model introduced here.

Keywords

Boundary Element Method Smooth Point Aerodynamic Modeling Helicopter Rotor Pitch Mode 
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References

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    Johnson, W., (1980), “Helicopter Theory,” Princeton University Press, Princeton NJ.Google Scholar
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Copyright information

© Springer-Verlag Berlin Heidelberg 1990

Authors and Affiliations

  • F. Mastroddi
    • 1
  • L. Morino
    • 1
  1. 1.Università di Roma “La Sapienza”RomeItaly

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