Author:
ILIE Marcel, ,Semenescu Augustin,
Abstract
The present research concerns the helicopter aerodynamics and the blade-vortex interaction phenomenon. The computational studies are carried out using the large-eddy simulation approach for subsonic incompressible flow of Reynolds number Re=1.3x106. The helicopter aerodynamics is dominated by the blade-vortex interaction (BVI) phenomenon which is responsible for noise and vibrations. During the helicopter flight, a tip-vortex filament is formed and its interaction with the advancing blade causes the blade-vortex interaction phenomenon. The study shows that the blade-vortex interaction causes oscillations of the aerodynamic coefficients. Due to the turbulence phenomenon, the oscillations exhibit a non-linear behaviour.
Publisher
Academia Oamenilor de Stiinta din Romania
Reference19 articles.
1. [1] Abelló, J. C., and George, A.R., 1999. Rotorcraft BVI Noise Reduction by Attitude Modification, 5th AIAA/CEAS Aeroacoustics Conference, Bellevue, Washington, May, 10-12
2. [3] Abello, J., George, A., 2003. Wake Displacement Study of Attitude and Flight Parameter Modifications to Reduce Rotorcraft Blade-Vortex Interaction (BVI) Noise, 9th AIAA/CEAS Aeroacoustics Conference, Hilton Head, SC, May 12-14
3. [4] Caradonna, F. X., Kitaplioglu, C., and McCluer, M., 1999, An Experimental Study of Parallel Blade-Vortex Interaction Aerodynamics and Acoustics Utilizing an Independently Generated Vortex," NASA Ames Research Center, TM 199208790, Moffett Field, CA
4. [5] M. Ilie, A. Semenescu, G. Liliana Stroe, S. Berbente, Numerical Computations of the cavity flow using the potential flow theory, Annals of the Academy of Romanian Scientists Series on Engineering Sciences, Volume 13, Number 2/2021, ISSN 2066-8570
5. [6] M. Ilie. "A computational model for cardiovascular hemodynamics and protein transport phenomena", Health and Technology, 2021