Final maximum lift coefficients for three airfoils tested with 0.20cw flap were about equal; increase in minimum profile drag coefficient with airfoil thickness was large, being about twice as great for NACA 23030 as for 23012 plain foil.
Wind-tunnel investigation of N.A.C.A. 23012, 23021, and 23030 airfoils with various sizes of split flap
Nat Advisory Committee Aeronautics -- Report
1939
13 pages
Bibliography
Report
English
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Pressure distribution over N.A.C.A. 23012 airfoil with N.A.C.A. 23012 external-airfoil flap
Engineering Index Backfile | 1938
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