Rotor blade-vortex interaction impulsive noise source localization

AIAA Journal ◽  
1990 ◽  
Vol 28 (4) ◽  
pp. 593-600 ◽  
Author(s):  
W. R. Splettstoesser ◽  
K. J. Schultz ◽  
Ruth M. Martin
Keyword(s):  
Source Localization ◽  
Rotor Blade ◽  
Noise Source ◽  
Impulsive Noise ◽  
Vortex Interaction ◽  
Blade Vortex Interaction

scholarly journals Helicopter Model Rotor‐Blade Vortex Interaction Impulsive Noise: Scalability and Parametric Variations

1987 ◽  
Vol 32 (1) ◽  
pp. 3-12 ◽  
Author(s):  
D. A. Boxwell ◽  
F. H. Schmitz ◽  
W. R. Splettstoesser ◽  
K. J. Schultz
Keyword(s):  
Rotor Blade ◽  
Impulsive Noise ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Model Rotor

Development and validation of a hybrid method for predicting helicopter rotor impulsive noise

2018 ◽  
Vol 233 (4) ◽  
pp. 1323-1339 ◽  
Author(s):  
Liangquan Wang ◽  
Guohua Xu ◽  
Yongjie Shi
Keyword(s):  
Hybrid Method ◽  
High Speed ◽  
Stokes Equations ◽  
Impulsive Noise ◽  
Computational Cost ◽  
Helicopter Rotor ◽  
Aerodynamic Load ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Hybrid Solver

Prediction of helicopter rotor impulsive noise is practically a very challenging task. This paper describes a hybrid method to predict rotor impulsive noise for both high-speed impulsive noise and blade–vortex interaction noise. The hybrid solver has been developed by combining the advantages of three different methods: (1) a computational fluid dynamics method based on Reynolds-averaged Navier–Stokes equations to account for the viscous and compressible effects near the blade; (2) a vorticity transport model to predict rotor wake system without artificial dissipation; and (3) an acoustic calculation method, based on Ffowcs-Williams Hawkings equation implemented to a permeable data surface. The developed hybrid solver is validated through available test data, for the cases of UH-1H model rotor, AH-1 Operational Loads Survey rotor, and Helishape 7A rotor. Peak sound pressure level of high-speed impulsive noise is accurately predicted with relative errors less than 7%. Additionally, acoustic waveform of blade–vortex interaction noise is well captured though it is sensitive to small changes in aerodynamic load. It is suggested that present hybrid method is versatile for the prediction of rotor impulsive noise with moderate computational cost.

Calculation of Rotor Blade-Vortex Interaction Airloads Using a Multiple-Trailer Free-Wake Model

10.2514/1.130 ◽  
2003 ◽  
Vol 40 (6) ◽  
pp. 1123-1130
Author(s):  
Joon W. Lim ◽  
Yung H. Yu ◽  
Wayne Johnson
Keyword(s):  
Rotor Blade ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Wake Model ◽  
Free Wake

Calculation of Rotor Blade-Vortex Interaction Airloads Using a Multiple-Trailer Free-Wake Model

2003 ◽  
Vol 40 (6) ◽  
pp. 1123-1130 ◽  
Author(s):  
Joon W. Lim ◽  
Yung H. Yu ◽  
Wayne Johnson
Keyword(s):  
Rotor Blade ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Wake Model ◽  
Free Wake
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