An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47° sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel /
Ralph P. Bielat, Daniel E. Harrison, and Domenic A. Coppolino.

Description

Main Author

Bielat, Ralph P.

Related Names

Coppolino, Domenic A.
Harrison, Daniel E.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, [1951]

Subjects

Wind tunnel testing.
Lift (Aerodynamics)
Drag (Aerodynamics)
Charts, diagrams, etc.
Airplanes > Airplanes / Wings, Swept-back.
Airplanes > Airplanes / Fuselage.
Aerodynamics, Transonic.
Diagrams.
Fuselages.
Charts, diagrams, etc.
Wind tunnel testing.
Drag (Aerodynamics)
Lift (Aerodynamics)
Aerodynamics, Transonic.
Airplanes > Airplanes / Fuselage.
Airplanes > Airplanes / Wings, Swept-back.

Summary

Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.

Note

NACA Research Memorandum L51I04a.
"October 31, 1951."
Cover title.

Physical Description

38 pages : illustrations ; 27 cm.

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