Investigation carried out in NACA 7-ft by 10-ft wind tunnel; results obtained given in form of diagrams showing chordwise distribution of pressure on both airfoil and flap and as plots of calculated aerodynamic coefficients for both airfoil and flap.
Pressure distribution over clarke Y-H airfoil section with split flap
Nat Advisory Committee Aeronautics -- Tech Note
1937
5 pages
6 Supp plates, Bibliography
Report
Englisch
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Pressure distribution over clarke Y-H airfoil section with split flap
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