Downwash Characteristics and Vortex-sheet Shape Behind a 63 Degree Swept-back Wing-fuselage Combination at a Reynolds Number of 6,100,000An 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. |
Common terms and phrases
0.25 mean aerodynamic 1.0 Distance 630 SWEPT-BACK WING 71 semispans aft aerodynamic chord point angles of attack aspect ratio 3.5 b/2 Distance boundary-layer control CHARACTERISTICS AND VORTEX characteristics and vortex-sheet chord plane extended COMBINATION AT REYNOLDS Committee for Aeronautics diagrs distance from chord Distance from plane DOWNWASH CHARACTERISTICS Downwash-angle contour maps experimental downwash angles experimentally determined extended chord FUSELAGE COMBINATION lift coefficient located between 0.57 Longitudinal distance aft longitudinal station maps are presented mean aerodynamic chord NACA 8 9 NACA RM A52J08 National Advisory Committee nine vertical transverse plane of symmetry planes and angles point for three presented for nine RESTRICTED The downwash Reynolds number RM A52J08 NACA rolled-up sheet sheet is presented SHEET SHAPE survey apparatus survey plane swept-back wing-fuselage combination three angles tip vortices Tolhurst transverse planes located vent separation vertical transverse planes vey planes vortex-sheet shape William H wing of aspect wing trailing edge Wing-Fuselage Combi