Some effects of spanwise aileron location and wing structural rigidity on the rolling effectiveness of 0.3-chord flap-type ailerons on a tapered wing having 63 degrees sweepback at the leading edge and NACA 64A005

H. Kurt Strass, E. M. Fields, Eugene D. Schult
naca-rm-l51d18a
Jun 1951


Some effects of aileron spanwise location and wing structural rigidity on the rolling power of 0.3-chord plain, flap-type ailerons on a wing with a taper ratio of 0.25, and aspect ratio of 3.5, and swept back 63 degrees at the leading edge have been investigated by the Langley Pilotless Aircraft Research Division by th use of rocket-propelled test vehicles.

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