Data obtained at six spanwise stations of wing; pressure plots presented for Mach number range from 0.20 to 0.60 and for angle of attack range from -4° to stalling angle of attack.
Chordwise pressure distributions on 12-foot-span wing of NACA 66-series airfoil sections up to Mach number of 0.60
Nat Advisory Committee Aeronautics -- Tech Note
1948
147 pages
Report
English
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