Abstract:
A method of calculating the velocity distribution in incompressible flow on annular aerofoils of moderate thickness/chord ratio and camber, and reasonably large radius/chord ratio (the order of 1 or greater), is developed, based on the use of distributions of singularities on a cylinder whose velocity fields are tabulated here. The annular wing at zero incidence is treated first, and then the wing at incidence. Examples of the calculated velocity distributions on various aerofoils are given.
