Method enables determination of form and magnitude of incremental normal force distribution to be made for airfoil flap combination for which section characteristics have been determined.
Calculation of chordwise load distribution over airfoil sections with plain, split, or serally hinged trailing-edge flaps
Nat Advisory Committee Aeronautics -- Report
1938
16 pages
Bibliography
Report
Englisch
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Engineering Index Backfile | 1938
|Engineering Index Backfile | 1938
|Unsteady Airfoil with Dynamic Leading- and Trailing-Edge Flaps
Online Contents | 2009
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