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Wind Tunnel Tests of Ailerons at Various Speeds I : Ailerons of 0.20 Airfoil Chord and True Contour with 0.35 Aileron-chord Extreme Blunt Nose Balance on the NACA 66,2-216 AirfoilHinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
Document ID
19930092929
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
Authors
Letko, W (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Denaci, H. G. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Freed, C (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1943
Subject Category
Aerodynamics
Report/Patent Number
NACA-WR-L-431
NACA-ACR-3F11
Accession Number
93R22219
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
FLYING, HIGH-SPEED
CONTROL STICKS-FORCES
AILERONS, BALANCED - SEALED-GAP
AILERONS - WIND TUNNEL TESTS
AILERONS, BALANCED - HINGE MOMENTS
PRESSURE DISTRIBUTION-AIRFOILS-NACA 66,2-216
AIRFOILS-NACA 66,2-216-CHAR , MOMENTS & ORDINATES LOW-DRAG
MACH NUMBER
WIND TUNNEL TESTS-NACA-STABILITY

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