Formula derived for pressure distribution under assumption of ratio of span to average chord (aspect ratio) that is not too small; range of validity of formula, so far as aspect ratio limitations are concerned, is not less than range of validity of lifting line theory for non-oscillating wing.
Effect of finite span on airload distributions for oscillating wings -- I: aerodynamic theory of oscillating wings of finite span
Nat Advisory Committee Aeronautics -- Tech Note
1947
39 pages
Report
English
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