Wind-tunnel investigation of control-surface characteristics.
XXIII,
a 0.25-airfoil-chord flap with tab having a chord twice the flap chord on an NACA 0009 airfoil /
by M. Leroy Spearman.
Description
- Language(s)
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English
- Published
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Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1945.
- Summary
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Summary: Wind-tunnel tests have been made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with a plain flap having a chord 25 percent of the airfoil chord and a balancing tab having a chord 50 percent of the airfoil chord or 200 percent of the flap chord so linked that the tab would deflect at a given rate with respect to the flap. Three linkage ratios were tested on the model. The tests indicated that the flap and tab could be linked to give hinge-moment balance with flap deflection and with angle of attack and yet have greater lift effectiveness than a plain flap of similar size with a conventional balancing tab having a chord 20 percent of the flap chord linked to give hinge-moment balance with flap deflection only.
- Note
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"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."
"Report date September 1945."
"Originally issued September 1945 as Advance Restricted Report L5G25."
"Report no. L-47."
Also available in electronic format.
- Physical Description
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14, [46] p. :
ill. ;
28 cm.
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