Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps (1939)
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eio represents maximum-lift increment for the split flap increases the profile-drag coefficient for the airfoil section cor- more rapidly with flap deflection and reaches an appre- rected from the older profile-drag coefficient CDa by ciably higher value than that for the plain flap. The… … Angle of attack, ot, deg. Figure L.—lift for the N. A. C. A. 23012 rectangular wuig of aspect ratio 6 with 0 JOc fall-span plain flap. tests in the N. A. C. A. 7- by 10-foot tunnel (reference the effective Reynolds Number. The methods of cor- 5). German tests (reference 6) of the N. A. C. A.…
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