Dynamic Stall Alleviation Using a Deformable Leading Edge Concept-A Numerical Study
Author:
Affiliation:
1. Georgia Institute of Technology, Atlanta, Georgia 30332-0150
2. Naval Postgraduate School, Monterey, California 93943
3. NASA Ames Research Center, Moffett Field, California 94035-1000
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.3060
Reference12 articles.
1. The effect of a leading-edge slat on the dynamic stall of an oscillating airfoil
2. Unsteady aerodynamic characteristics of a dual-element airfoil
3. Numerical analysis of aerodynamic performance of rotors with leading edge slats
4. Oscillatory Blowing: A Tool to Delay Boundary-Layer Separation
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