Gust-tunnel investigation of a flexible-wing model with semichord line swept back 45° /
Thomas D. Reisert.

Description

Main Author

Reisert, Thomas D.

Related Names

United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

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

Subjects

Wind tunnel testing.
Gust loads.
Bending moment.
Airplanes > Airplanes / Wings, Swept-back.
Airplanes > Airplanes / Models > Airplanes / Models / Wings.
Wind tunnel testing.
Bending moment.
Gust loads.
Airplanes > Airplanes / Wings, Swept-back.
Airplanes > Airplanes / Models > Airplanes / Models / Wings.

Summary

An investigation was made in the Langley gust tunnel of a flexible-wing model with the semichord line swept back 45 degrees to obtain experimental data on the amount of gust-load alleviation that might be expected as a result of the wings flexing under load. The results indicated that unless adverse pitching motion could be eliminated or reduced the over-all load reduction would be small. The net reduction in bending moment, however, may be appreciable.

Note

NACA TN No. 1959.
"October 1949."

Physical Description

13 pages : illustrations ; 28 cm.

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