A comparison of some finite element and finite difference methods for a simple sloshing problem
Author:
Affiliation:
1. Southwest Research Institute, San Antonio, Texas
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.6480
Reference9 articles.
1. Rao, D. M. "Hypersonic Control Effectiveness Studies on Delta Wings with Trailing-Edge Flap," Ph.D. thesis,1970, Uni. of London,England.
2. Shock interaction effect on a flapped delta wing at M equals 8.2
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2. On the sloshing of liquids in parallelepiped-shaped containers;European Journal of Physics;2003-03-28
3. Mixing fluids and solids;Nature;1995-08
4. Errata: "A Comparison of Some Finite Element and Finite Difference Methods for a Simple Sloshing Problem";AIAA Journal;1982-06
5. ADDITIONAL APPLICATIONS AND GENERALIZATION OF THE FINITE ELEMENT METHOD;The Finite Element Method in Engineering;1982
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