Compact Difference Scheme Applied to Simulation of Low-Sweep Delta Wing Flow.
Author:
Affiliation:
1. U.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433-7512
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.5403
Reference44 articles.
1. Vortex flows over fixed-wing micro air vehicles
2. Leading-Edge Vortex Structure of Nonslender Delta Wings at Low Reynolds Number
3. Flow developments above 50-deg sweep delta wings with different leading-edge profiles
4. Further development of a Navier-Stokes solution procedure based on higher-order formulas
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