A new approach for aerodynamic and aeroacoustic analysis of actively controlled flaps (ACF) rotor is established to predict airloads and noise reduction. The approach is divided into three parts. The first is an unsteady aerodynamic model of the ACF described through a panel method, and the unsteady pressure under interaction of rotor tip vortex and ACF trailing-edge vortex, which are depicted through a viscous vortex particle method, are taken into account. The second is the influence of the ACF on trajectory of the wake and ACF trailing-edge vortex, which is carried out by a new imaged vortex model to capture blade-vortex interaction (BVI). The third is an aeroacoustic model coupled into the aerodynamic model by transmitting the unsteady pressure to Ffowcs Williams and Hawkings (FW-H) equation. The present approach is applied to AH-1G rotor, and the results show that the predicted unsteady airloads, high-speed impulsive (HSI), and BVI noise are compared favorably with experiment and Reynolds-averaged Navier–Stokes (RANS)/FW-H results. Finally, the variation of airload and noise reduction of ONERA Active Blade Concept rotor (ABC) is predicted and compared with experiment. It is shown that the present approach predicts the airload and noise reduction of the ACF with different phases and flap locations with good accuracy.
New Approach for Aerodynamic and Aeroacoustic Analysis of Actively Controlled Flaps Rotor
Journal of Aircraft ; 55 , 6 ; 2191-2202
01.11.2018
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Helicopter rotor aerodynamic and aeroacoustic environments
Tema Archiv | 1977
|Dynamics of a Rotor Controlled by Aerodynamic Servo Flaps
Emerald Group Publishing | 1959
|Helicopter Noise Reduction By Actively Controlled Flaps
AIAA | 2005
|