Wing tested with full span and partial span split flaps deflected 60° and without flaps; leading edge roughness tests made with flaps retracted configuration; some chordwise pressure distribution measurements made for all flap configurations of model.
Effects of Mach number and Reynolds number on maximum lift coefficient of wing of NACA 230-series airfoil sections
Nat Advisory Committee Aeronautics -- Tech Note
1947
14 pages
26 Supp plates, Bibliography
Report
English
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Engineering Index Backfile | 1950
|Engineering Index Backfile | 1952
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