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Preliminary Wind-Tunnel and Flight Tests of a Balanced Split Flap, Special ReportOne disadvantage that has been apparent in the operation of split flaps as used to date is the time and effort required to operate them. In this communication an investigation is being made of possible means for balancing them aerodynamically to make their operation easier. Several arrangements have been tested in the 7 by 210 foot wind tunnel, and the results of the wind-tunnel tests as well as preliminary flight tests on one of the more promising forms are given in this paper.
Document ID
20090015107
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Weick, Fred E. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Thompson, Floyd L. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 1934
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-SR-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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