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An analytical model leading to the pressure distribution on the cross section of a Darrieus Rotor Blade (airfoil) was constructed. The model was based on the inviscid flow theory and the contribution of the nonsteady wake vortices was neglected. The analytical model was translated into a computer code in order to study a variety of boundary conditions encountered by the rotating blades of the Darrieus Rotor. The results of the program indicate that for a pitching airfoil, lift can be adequately approximated by the Kutta-Joukowski forces, despite notable deviations in the pressure distribution on the airfoil. These deviations are most significant at the upwind half of the Darrieus Rotor where higher lift is accompanied by increased adverse pressure gradients. It was also found that the effect of pitching on lift can be approximated by a linear shift in the angle of attack proportional to the blade angular velocity. Finally, the fluid velocity about the pitching-only NACA 0015 was tabulated; thus allowing the principle of superposition to be used in order to determine the fluid velocity about a translating and pitching airfoil. / Graduation date: 1984

Thesis (M. Phil.)--Hong Kong University of Science and Technology, 2002. / Includes bibliographical references (leaves 54-57). Also available in electronic version. Access restricted to campus users.

Thesis (M.S.)--West Virginia University, 2004. / Title from document title page. Document formatted into pages; contains vi, 101 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 41-45).

Thesis (Ph. D.)--Lehigh University, 2003. / Includes vita. Includes bibliographical references (leaves 264-274).

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