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The effects of full-span and partial-span split flaps on the aerodynamic characteristics of a tapered wingThe investigation was made to determine the effects of full-span and of partial-span split flaps on the aerodynamic characteristics of a tapered wing. Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a highly tapered Clark Y wing equipped with various split flaps. Two sizes of tapered-chord flaps were tested as full-span flaps, and a narrow tapered-chord flap was tested as a partial-span flap by cutting off portions first from the tip and then from the center. The investigation showed that with full-span split flaps the lift and drag characteristics of the tapered wing up to the stall are similar to those of a rectangular wing with flaps of comparable size, but that the stall of the tapered wing with full-span flaps occurs at progressively lower angles of attack with increasing flap deflection up to that for maximum lift. For partial-span tapered split flaps on a tapered wing it was found that the maximum lift is greater, and the lift-drag ratio at maximum lift is less, when the partial-span flap is located at the center of the wing than when it is located at the tip portion.
Document ID
19930081271
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Wenzinger, Carl J
Date Acquired
September 6, 2013
Publication Date
September 1, 1934
Report/Patent Number
NACA-TN-505
Accession Number
93R10561
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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