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An Analysis of the Effect of Structural Feedback on the Flutter of a Control Surface Having a Power-Boost System
From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."
Date:
June 10, 1952
Creator:
Barnes, Robert H.
System:
The UNT Digital Library