Downwash Characteristics and Vortex-sheet Shape Behind a 63 Degree Swept-back Wing-fuselage Combination at a Reynolds Number of 6,100,000
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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0.25 mean aerodynamic aerodynamic chord point Airplanes amount angles of attack aspect ratio assumed aua/d boundary-layer control CHARACTERISTICS AND VORTEX characteristics and vortex-sheet COMBINATION COMBINATION AT REYNOLDS Committee for Aeronautics Complete corrected December diagrs displacement distance distribution downwash angles DOWNWASH CHARACTERISTICS effect experimental extended feet Figure flat fuselage FUSELAGE COMBINATION longitudinal mean aerodynamic chord NACA RM A52J08 National Advisory Committee nine vertical transverse obtained plane of symmetry planes and angles point for three position predicting presented presented for nine reference RESTRICTED NACA RM Reynolds number roll sheet is presented SHEET SHAPE span Stability survey apparatus Sweep swept-back wing Theoretical theory three angles Tolhurst transverse planes located tunnel various vertical transverse planes vortex sheet vortex-sheet shape Wake William H wing of aspect Wing-Fuselage Combi ее шоу