A modified vortex lattice method is developed to solve for the nonlinear three-dimensional unsteady incompressible flow over delta wings. Symmetric motions (pitching, heaving) and asymmetric motions (roll, yaw) are considered. Then the method is generalized to treat the nonlinear three-dimensional steady flow for bodies and wing body combinations. Numerical examples include variety of shapes and comparison with existing experimental data and other numerical methods over a wide range of angle of attack shows good agreement. For bodies alone the results deteriorate downstream of the separation region, while for wing-body combinations the agreement with the experimental data is good as long as the body separation effect is not large. The developed computer codes should provide a useful tool in the design of aircraft and missiles. / Ph. D.
| Identifer | oai:union.ndltd.org:VTETD/oai:vtechworks.lib.vt.edu:10919/38729 |
| Date | 08 July 2010 |
| Creators | Atta, Essam H. |
| Contributors | Engineering Science and Mechanics, Nayfeh, Ali H., Kaiser, John E. Jr., Mook, Dean T., Hansgen, Kenneth B., Kandil, Osama A. |
| Publisher | Virginia Tech |
| Source Sets | Virginia Tech Theses and Dissertation |
| Language | English |
| Detected Language | English |
| Type | Dissertation, Text |
| Format | 118 leaves, BTD, application/pdf, application/pdf |
| Rights | In Copyright, http://rightsstatements.org/vocab/InC/1.0/ |
| Relation | OCLC# 08057064, LD5655.V856_1978.A88.pdf |
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