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Comparative wind tunnel test at high Reynolds numbers of NACA 64 621 airfoils with two aileron configurationsAn experimental program to measure the aerodynamic characteristics of the NACA 64-621 airfoil when equipped with plain ailerons of 0.38 chord and 0.30 chord and with 0.38 chord balanced aileron has been conducted in the pressurized O.S.U. 6 x 12 ft High Reynolds Number Wind Tunnel. Surface pressures were measured and integrated to yield lift and pressure drag coefficients for angles of attack from -3 to +42 deg and for selected aileron deflections from 0 to -90 deg at nominal Mach and Reynolds numbers of 0.25 and 5 x 10(exp 6). When resolved into thrust coefficient for wind turbine aerodynamic control applications, the data indicated the anticipated decrease in thrust coefficient with negative aileron deflection at low angles of attack; however, as angle of attack increased, thrust coefficients eventually became positive. All aileron configurations, even at -90 deg deflections showed this trend. Hinge moments for each configuration complete the data set.
Document ID
19950021556
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gregorek, G. M. (Ohio State Univ. Columbus, OH, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1995
Publication Information
Publication: DASCON Engineering, Collected Papers on Wind Turbine Technology
Subject Category
Aerodynamics
Meeting Information
Meeting: DOE/NASA Workshop on Horizontal Axis Wind Turbine Technology
Location: Cleveland, OH
Country: United States
Start Date: May 8, 1984
End Date: May 10, 1984
Accession Number
95N27977
Funding Number(s)
CONTRACT_GRANT: NAG3-330
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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