Coupled Aeroelastic Prediction of the Effects of Leading-Edge Slat on Rotor Performance
Author:
Affiliation:
1. Department of Mechanical Engineering, University of Wyoming, Laramie, Wyoming 82071
2. Department of Aerospace Engineering, University of Maryland, College Park, Maryland 20742
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.C033236
Reference21 articles.
1. BousmanW. G. “Airfoil Dynamic Stall and Rotorcraft Maneuverability,” NASA TR-TM-2000-209601, July 2000.
2. Computational Investigation of Trailing Edge Flap for Control of Vibration
3. Dynamic Stall Alleviation Using a Deformable Leading Edge Concept-A Numerical Study
4. Compressible Dynamic Stall Performance of a Variable Droop Leading Edge Airfoil with a Gurney Flap
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