Investigation of wing-tip ailerons on a 51.3 degrees sweptback wing at transonic speeds by the transonic-bump method

William C. Moseley, Jr., James M. Watson
naca-rm-l51h27
Nov 1951


An investigation to determine the aerodynamic characteristics of deflectable wing-tip ailerons on a sweptback wing was made in the Langley high-speed 7- by 10-food tunnel by means of the transonic-bump technique. The basic wing used in this investigation had 51.3 degree sweepback at the leading edge, an aspect ratio of 2.87, and a taper ratio of 0.51.

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