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High-Speed Load Distribution on the Wing of a 3/16-Scale Model of a Scout-Bomber Airplane with Flaps DeflectedThe tests reported herein were made for the purpose of determining the high-speed load distribution on the wing of a 3/16 scale model of a scout-bomber airplane. Comparisons are made between the root bending-moment and section torsional-moment coefficients as obtained experimentally and derived analytically. The results show good correlation for the bending-moment coefficients but considerable disagreement for the torsional-moment coefficients.
Document ID
20030063941
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Barnes, Robert H. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
August 21, 1947
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-A7D23
Report Number: NACA-RM-A7D23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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