Damping-in-roll calculations for slender swept-back wings and slender wing-body combinations /
Harvard Lomax and Max A. Heaslet.

Description

Main Author

Lomax, Harvard.

Related Names

Heaslet, Max A.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

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

Subjects

Mathematical analysis.
Aspect ratio (Aerofoils)
Roll (Aerodynamics)
Aerofoils.

Summary

The damping-in-roll parameter is calculated theoretically for triangular wings on cylindrical bodies and for a class of wings with swept-back plan forms. The analysis is based on the usual assumptions of linearized compressible-flow theory together with the added restriction that at the free-stream Mach number the product and the streamwise velocity gradient is amall. The accuracy of the results is tested by a comparison with the exact solution of the linearized equation for a triangular wing and for such plan forms is shown to increase as reduced aspect ratio decreases.

Note

NACA TN No. 1950.
"September 1949."

Physical Description

32 p. : ill. ; 28 cm.

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