An investigation was conducted with 73-Percent-semispan inboard spoiler ailerons, projecting 4 percent of the local chord from the wing surface, and located at the 70-percent-chord line of a 45° sweptback-wing—fuselage combination. The model consisted of a wing with an aspect ratio of 3.98, taper ratio of 0.6l, and NACA 65AOO6 airfoil sec-tions parallel to the plane of symmetry in combination with a fuselage of fineness ratio 10. Pressure data were measured on the wing and spoiler at several spanwise stations at Mach numbers from 0.60 (Reynolds number 5.1 x 10°) to 1.03 (Reynolds number 6.2 X 106) for angles of attack that usually extended to 20° or more.
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