Results of wind-tunnel tests made as part of investigation of lateral control devices; spoilers with chords up to 15.0% of wing chord tested in several locations on plain rectangular wing, and in two locations on same wing equipped with 20.0% chord split flap down 60°.
Effect of retractable-spoiler location on rolling- and yawing-moment coefficients
Nat Advisory Committee Aeronautics -- Tech Notes
1934
12 pages
5 Supp plates, Bibliography
Report
Englisch
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Semiempirical method for estimating rolling moment due to yawing of airplanes
Engineering Index Backfile | 1949
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