Rotor blade response based on CFD in the frequency domain

M. Kumar, V. R. Murthy

Research output: Chapter in Book/Report/Conference proceedingConference contribution

5 Scopus citations

Abstract

A formulation to determine the aeroelastic response of a rotor in forward flight is presented. The aerodynamic forces arising in the steady periodic state have been calculated using a frequency domain based CFD analysis in multiblade coordinates. The CFD model is coupled with a nonlinear finite element model of a rotor also in multiblade coordinates. The formulation is quite general and any fluid model governed by equations such as RANS, Euler or Hybrid can be used in the computations. The transformation to multiblade coordinates leads to the cancellation of harmonics except at the blade passage frequencies, thereby increasing the efficiency of the technique. The formulation is being implemented in a computer code and as of today the CFD solution in the frequency domain has been validated by comparing with the available experimental and numerical results.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Pages5083-5126
Number of pages44
StatePublished - 2006
Event44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV, United States
Duration: Jan 9 2006Jan 12 2006

Publication series

NameCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Volume7

Other

Other44th AIAA Aerospace Sciences Meeting 2006
CountryUnited States
CityReno, NV
Period1/9/061/12/06

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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