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Interference Effects in an Infinite Cascade of Wings of Finite Span
Published online by Cambridge University Press: 04 July 2016
Extract
Using Glauert's three-dimensional aerofoil theory, an expression for the induced velocity due to the trailing vortices of an infinite cascade of wings of finite span has been derived. The reduction in the average lift coefficient due to these induced velocities has been evaluated for some cases. It is shown that for a cascade of low space-chord ratio, the reduction in lift due to the interference from the trailing vortices is quite considerable.
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- Copyright © Royal Aeronautical Society 1962
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