Numerical Investigation of Reynolds Number Effects on a Blunt Leading-Edge Delta Wing
Author:
Affiliation:
1. Royal Institute of Technology
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2006-3001
Reference16 articles.
1. Reynolds number and leading-edge bluntness effects on a 65-deg delta wing
2. Analysis of PSP Results Obtained for the VFE-2 65° Delta Wing Configuration at Sub- and Transonic Speeds
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