The effect of a change in airfoil section on the hinge-moment characteristics of a half-delta tip control with a 60° sweep angle at a Mach number of 6.9 /
by David E. Fetterman and Herbert W. Ridyard.

Description

Main Author

Fetterman, David E.

Related Names

Ridyard, Herbert W.
United States. National Adviosry Committee for Aeronautics.
Langley Aeronautical Laboratory.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1954.

Subjects

Airplanes > Airplanes / Control surfaces.
Aerofoils.
Airplanes > Airplanes / Control surfaces.
Aerofoils.

Note

"October 15, 1954."

Physical Description

14 pages : illustrations ; 27 cm

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