Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35°, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section.
Transonic-bump method /
Robert F. Thompson.

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Main Author
Thompson, Robert F.
Related Names
United States. National Adviosry Committee for Aeronautics.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.
Language(s)
English
Published
Washington, D.C. : National Advisory Committee for Aeronautics, 1950.
Subjects
Wind tunnel testing.
Flaps (Airplanes)
Charts, diagrams, etc.
Airplanes > Wings, Swept-back.
Airplanes > Models > Wings.
Airplanes > Control surfaces.
Airplanes > Control.
Aerofoils > Testing.
diagrams.
Charts, diagrams, etc.
Wind tunnel testing.
Aerofoils > Testing.
Airplanes > Control.
Flaps (Airplanes)
Airplanes > Models > Wings.
Airplanes > Control surfaces.
Airplanes > Wings, Swept-back.
Summary
This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.
Note
NACA Research Memorandum L9L12a.
"January 25, 1950."
Cover title.
Physical Description
22 pages : illustrations ; 27 cm.
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