Wind-tunnel investigation of damping in roll at supersonic speeds of triangular wings at angles of attack /
Russell W. McDearmon and Robert A. Jones.

Description

Main Author

McDearmon, Russell W.

Related Names

Jones, Robert A.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1956.

Subjects

Charts, diagrams, etc.
Wind tunnel testing.
Rolling (Aerodynamics)
Airplanes > Airplanes / Wings, Triangular.
Airplanes > Airplanes / Models > Airplanes / Models / Wings.
Airplanes > Airplanes / Models > Airplanes / Models / Testing.

Summary

Experimental values of the damping in roll of three triangular wings have been obtained at Mach numbers of 1.62, 1.94, 2.22, 2.41, and 2.62 over a range of angle of attack from approximately 0 to 13 degrees. The aspect ratios of the wings were 1.46, 2.31, and 3.35.

Note

NACA Research Memorandum L56F13A.
"September 14, 1956."
Title from cover.

Physical Description

32 p. : ill. ; 27 cm.

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