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Old 05-14-2005, 07:32 PM
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Default RE: Airfoils

The chord x span = area
The greater the chord for a given thickness, the greater the frontal area (and wing area)

I don't think your question is specific to airfoils, but to the whole wing?

Drag is directly proportional to wing area
Wings with higher aspect ratios have less induced drag

Lift increases slightly with thickness (up to a point)
The Lift at any given angle of attack (and the lift/drag ratio) increases with camber (curvature of the mean line), up to a point

The lift slope of all airfoils (lift per degree angle of attack) is practically the same, affected by wing planform and aspect ratio

Wings of rectangular planform have a slightly reduced lift slope
Wings of low aspect ratio have reduced lift slope
Swept wings have reduced lift slope