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- W606191431 abstract "An investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5 and the airfoil sections normal to the quarter-chord line were NACA 61(sub 1)-A112. Tests included the plain wing and the wing with various combinations of extensible leading-edge and split flaps. The investigation was made to determine the effect of boundary-layer control by suction on the aerodynamic characteristics in yaw and on the effectiveness of a split-flap-type aileron for a range of angle of attack and suction-flow coefficient at a Reynolds number of 4.2 x 10 (exp 6) corresponding to a Mach number of approximately 0.07." @default.
- W606191431 created "2016-06-24" @default.
- W606191431 creator A5017640015 @default.
- W606191431 date "1948-10-28" @default.
- W606191431 modified "2023-09-27" @default.
- W606191431 title "The Effect of Boundary-layer Control by Suction and of Several High-lift Devices on the Aerodynamic Characteristics in Yaw of a 47.5 Degree Sweptback" @default.
- W606191431 hasPublicationYear "1948" @default.
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