Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section.
Transonic-bump method /
William C. Sleeman, Jr., and Robert E. Becht.

Description

Main Author

Sleeman, William C.

Related Names

Becht, Robert E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1949.

Subjects

Charts, diagrams, etc.
Wind tunnel testing.
Pitching (Aerodynamics)
Drag (Aerodynamics)
Lift (Aerodynamics)
Aerofoils > Aerofoils / Testing.
Airplanes > Airplanes / Wings, Swept-back.
Airplanes > Airplanes / Wings, Triangular.

Summary

This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.

Note

NACA Research Memorandum L9G22A.
"September 6, 1949."
Title from cover.

Physical Description

29 p. : ill. ; 27 cm.

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