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
| Identifer | oai:union.ndltd.org:ORGSU/oai:ir.library.oregonstate.edu:1957/35533 |
| Date | 28 September 1983 |
| Creators | Ghodoosian, Nader |
| Contributors | Wilson, Robert E. |
| Source Sets | Oregon State University |
| Language | en_US |
| Detected Language | English |
| Type | Thesis/Dissertation |
Page generated in 0.0018 seconds