INVESTIGATION OF SPOILER AILERONS WITH AND WITHOUT A GAP BEHIND THE SPOILER ON A 45° SWEPTBACK WING-FUSELAGE COMBINATION AT MACH NUMBERS FROM 0.60 TO 1.03

摘要

An investigation was conducted with several 73-pereent semispan inboard spoiler ailerons, projecting k- percent of the local wing 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 sections parallel to the plane of symmetry in combination with a "blunt-tail fuselage of fineness ratio 10. Six-component force data were obtained during the investigation in the Langley l6-foot transonicntunnel at Mach numbers from 0.60 (Reynolds number of 5.1 X 10°) to 1.03 (Reynolds number of 6.2 x 106) for an angle-of-attack range of approximately -2° to 26°.