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Wind-tunnel investigation of rectangular and tapered NACA 23012 wings with plain ailerons and full-span split flaps (1938)
NASA Technical Reports Server (NTRS) · leaf 20
« * * … Aileron deflection, 6a , deg. (a) Flap neutral fb) Flap at 0.65 (c) Flap at 0.85cw Figure 16.- Rolling-.yawing-, and hinge-moment coefficients of 0.15by 0.60 b/2 5:1 tapered plain aileron on 5:1 3 tapered wing with full-span O.ZOtv 5:1 tapered split flap deflected 60° ai two locations. 1—NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
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