Atta, Essam H.2014-03-142014-03-141978-05-06etd-07082010-020332http://hdl.handle.net/10919/38729A 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.118 leavesBTDapplication/pdfenIn CopyrightLD5655.V856 1978.A88Airplanes -- WingsAirplanes -- Wings, TriangularDissertationhttp://scholar.lib.vt.edu/theses/available/etd-07082010-020332/