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Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft CorporationWing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Document ID
19930092843
Acquisition Source
Headquarters
Document Type
Other - NACA Wartime Report
Authors
Abbott, Ira H (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1942
Subject Category
Aerodynamics
Report/Patent Number
NACA-WR-L-678
Report Number: NACA-WR-L-678
Accession Number
93R22133
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
PRESSURE DISTRIBUTION - AIRFOILS - DAVIS
WING FLAPS, FOWLER
WIND TUNNEL TESTS - NACA - PRESSURE, LOW-TURBULENCE (7 1/2' X 3')
PRESSURE DISTRIBUTION - WINGS - CONSOLIDATED B-32
WING FLAPS - FOWLER

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