Investigation conducted in Langley 19-ft pressure tunnel to determine some of effects of airfoil section and washout on maximum lift and stalling characteristics of 10%-thick wings.
Experimental and calculated characteristics of three wings of NACA 64-210 and 65-210 airfoil sections with and without 2° washout
Nat Advisory Committee Aeronautics -- Tech Note
1947
17 pages
Report
Englisch
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