"This paper presents an analytical-numerical aerody-. namic\/aeroacoustic formulation for the analysis of the tonal noise emitted by helicopter rotors and propellers. It is particularly suited for those configurations dominated by local high-frequency changes (both in time and space) of blades inflow velocity. The solution of the Ffowcs Williams-Hawkings equation. for noise radiation prediction is combined with the frequency-domain Kussner-Schwarz formulation that yields the sectional, unsteady aerodynamic loads, starting from the knowledge of the downwash on the airfoil due to blade motion and inflow induced on it by any external source of perturbation. Here, the. blade inflow is assumed to be evaluated through a 3D, unsteady, panel method formulation suited for the analysis of rotors operating in a complex aerodynamic environment. This aerodynamic\/aeroacoustic model gives a computationally efficient solution procedure that may be conveniently applied in preliminary design\/multidisciplinary optimization applications. The. proposed approach is validated through comparison with the (accurate, but computationally expensive) acoustic field obtained through the blade pressure loads directly evaluated by the time-marching panel-method solver. The results are provided in terms. of blade loads, noise signatures and sound pressure level contours.. . "

Gennaretti, M., Testa, C., Bernardini, G., Anobile, A. (2012). An Analytical-Numerical Aerodynamic Formulation for Efficient Aeroacoustics Analysis of Rotorcraft. In Proceedings of the Internoise 2012/ASME NCAD meeting (peer-reviewed paper) [10.1115/NCAD2012-1081].

An Analytical-Numerical Aerodynamic Formulation for Efficient Aeroacoustics Analysis of Rotorcraft

GENNARETTI, MASSIMO;BERNARDINI, Giovanni;ANOBILE, ALESSANDRO
2012-01-01

Abstract

"This paper presents an analytical-numerical aerody-. namic\/aeroacoustic formulation for the analysis of the tonal noise emitted by helicopter rotors and propellers. It is particularly suited for those configurations dominated by local high-frequency changes (both in time and space) of blades inflow velocity. The solution of the Ffowcs Williams-Hawkings equation. for noise radiation prediction is combined with the frequency-domain Kussner-Schwarz formulation that yields the sectional, unsteady aerodynamic loads, starting from the knowledge of the downwash on the airfoil due to blade motion and inflow induced on it by any external source of perturbation. Here, the. blade inflow is assumed to be evaluated through a 3D, unsteady, panel method formulation suited for the analysis of rotors operating in a complex aerodynamic environment. This aerodynamic\/aeroacoustic model gives a computationally efficient solution procedure that may be conveniently applied in preliminary design\/multidisciplinary optimization applications. The. proposed approach is validated through comparison with the (accurate, but computationally expensive) acoustic field obtained through the blade pressure loads directly evaluated by the time-marching panel-method solver. The results are provided in terms. of blade loads, noise signatures and sound pressure level contours.. . "
978-079184532-5
Gennaretti, M., Testa, C., Bernardini, G., Anobile, A. (2012). An Analytical-Numerical Aerodynamic Formulation for Efficient Aeroacoustics Analysis of Rotorcraft. In Proceedings of the Internoise 2012/ASME NCAD meeting (peer-reviewed paper) [10.1115/NCAD2012-1081].
File in questo prodotto:
Non ci sono file associati a questo prodotto.

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11590/279325
Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 0
  • ???jsp.display-item.citation.isi??? ND
social impact