Tests of 10 by 60 in Clark Y main airfoil and NACA 0012 flap having chord equal to 15% of main wing chord; axis of flap in all cases was on flap chord and 20% back from its leading edge; no serious adverse change in lateral stability was found to result from use of flap in optimum position.
Wind-tunnel tests of wing with trailing-edge auxiliary airfoil used as flap
Nat Advisory Committee Aeronautics -- Tech Notes
1935
11 pages
Supp plates
Report
English
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