Downwash Characteristics and Vortex-sheet Shape Behind a 63 Degree Swept-back Wing-fuselage Combination at a Reynolds Number of 6,100,000

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National Advisory Committee for Aeronautics, 1952 - Aeronautics - 45 pages
An experimental investigation has been conducted to define the downwash field and vortex-sheet shape shape behind a large-scale wing-fuselage combination incorporating a 63 degree swept-back wing of aspect ratio 3.5. Data for nine vertical transverse planes located betwwn 0.57 and 2.71 semispans behind the 0.25 mean aerodynamic chord point are presented for three angles of attack at a Reynolds number of 6,100,000. The lift coefficient range was limited to that where no separation of the air flow across the wing existed, but reached as high as 0.52 with the aid of boundary-layer control.

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