Computational and Experimental Ice Accretions of Large Swept Wings in the Icing Research Tunnel
Author:
Affiliation:
1. University of Washington, Seattle
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2016-3734
Reference20 articles.
1. Iced-airfoil aerodynamics
2. A Hybrid Airfoil Design Method for Icing Wind Tunnel Tests
3. 3Anderson, D. N. “Manual of scaling methods,” NASA/CR-2014-212875 .
4. 3D Swept Hybrid Wing Design Method for Icing Wind Tunnel Tests
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