28th Congress of the International Council of the Aeronautical Sciences, 23 - 28 September 2012, Brisbane, Australia
Paper ICAS 2012-3.9.1
AEROACOUSTIC ANALYSIS OF A HELICOPTER CONFIGURATION WITH DUCTED TAIL ROTOR
J. H. You, N. Thouault, C. Breitsamter, N. A. Adams
Inst. Of Aerodynamics, TU Munich, Germany
Keywords: aeroacoustics, helicopter, ducted tail rotor, unsteady rans,fw-hanalogy
Numerical aeroacoustic investigations are carried out to understand the noise-generation mechanisms associated with the ducted tail rotor of a light weight class transport helicopter. The flow field is calculated using an Unsteady Reynolds Averaged Navier-Stokes approach. The Ffowcs Williams and Hawkings analogy is applied to compute the sound pressure field.
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