Downwash characteristics and vortex-sheet shape behind a 63 degree swept-back wing-fuselage combination at a Reynolds number of 6,100,000 /
by William H. Tolhurst, Jr.
Description
- Language(s)
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English
- Published
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Washington, D.C. : National Advisory Committee for Aeronautics, [1952].
- Summary
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It was found that at positie angles of attack the vortex sheet assumed a shape which was initially bowed upward but flattened out downstream before the rolling-up process had progressed to an appreciable degree. A comparison with theory showed that an acceptable approximation tothe downwash distribution within the distance surveyed could be obtained if the vortex sheet were assumed to be flat and the spanwise vorticity distribution were assumed to be that of the wing.
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.
- Note
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On front cover: "May 1954."
- Physical Description
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45 p. :
ill. ;
27 cm.
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