Experimental investigation of vortex breakdown over a sideslipping canard-configured aircraft model
Author:
Affiliation:
1. Naval Postgraduate School, Monterey, California 93943
2. Korean Air Force, Republic of Korea
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.46598
Reference12 articles.
1. Vortex Dynamics of Delta Wings
2. Unsteady aerodynamic characteristics of a fighter model undergoing large-amplitude pitching motions at high angles of attack
3. Pitch rate/sideslip effects on leading-edge extension vortices of anF/A-18 aircraft model
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1. Effect of Sideslip on High-Angle-of-Attack Vortex Flow over Close-Coupled Canard Configuration;Journal of Aircraft;2016-01
2. Eddy-Preserving Limiter for Unsteady Subsonic Flows;AIAA Journal;2012-02
3. Control of High-Incidence Vortical Flow on Double-Delta Wings Undergoing Sideslip;Journal of Aircraft;1997-07
4. Juncture fillets for vortex flow control on double-delta wings undergoing sideslip;34th Aerospace Sciences Meeting and Exhibit;1996-01-15
5. Effect of delta planform tip sail incidence and arrangement on wing performance;Journal of Aircraft;1995-09
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