An aeroacoustic model for high-speed, unsteady blade-vortex interaction
Author:
Affiliation:
1. Massachusetts Institute of Technology, Cambridge, Massachusetts
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.8233
Reference12 articles.
1. Helicopter Noise due to Blade‐Vortex Interaction
2. Unified aerodynamic-acoustic theory for a thin rectangular wing encountering a gust
3. High frequency thin-airfoil theory for subsonic flow
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