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Pressure Distribution Over a Rectangular Airfoil with a Partial-Span Split FlapThis report presents the results of pressure-distribution tests of a Clark y wing model with a partial-span split flap made to determine the distribution of air loads over both the wing and the flap. The model was used in conjunction with a reflection plane in the NACA 7 by 10 foot wind tunnel. The 20-percent-chord split flap extended over the inboard 60 percent of the semispan. The tests were made at various flap deflections up to 45 degrees and covered a range of angles of attack from zero lift to approximately maximum lift for each deflection.
Document ID
19930091646
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Wenzinger, Carl J
Harris, Thomas A
Date Acquired
September 6, 2013
Publication Date
January 1, 1937
Report/Patent Number
NACA-TR-571
Accession Number
93R20936
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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