Results indicated that gust load on sweptback wing airplanes was dependent on lift curve slope of equivalent straight wing multiplied by cosine of angle of sweep and on effect of gradual penetration of gust on unsteady lift function.
Tests of 45° sweptback-wing model in Langley gust tunnel
Nat Advisory Committee Aeronautics -- Tech Note
1948
25 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Tests of a 45° sweptback-wing model in the Langley gust tunnel
TIBKAT | 1948
|Tests of a Gust-Alleviating Wing in the Gust Tunnel
NTRS | 1941
|Tests of a gust-alleviating wing in the gust tunnel
TIBKAT | 1941
|