WER-16: Two-dimensional tests of four airfoils at angles of attack from 0 to 360 Degrees
Snyder, Melvin H.
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M.H.Snyder, W.H. Wentz, & A.Ahmed. Two-dimensional tests of four airfoils at angles of attack from 0 to 360 degrees. Wind Energy Report no.16. Wichita State University. Center for Energy Studies, 1984, 300 p.
Four airfoils; NACA 23030, 23024, 23018, and 64 3 -618; have been tested in the two-dimensional wind tunnel at Wichita State University at angles of attack from zero to 360 degrees. The 23024 airfoil was equipped with a 20% chord aileron and was tested at angles of aileron deflection from -60 degrees to +60 degrees. Airfoil characteristics in the form of coefficients of lift, drag, normal force, and leading-edge suction force, and coefficient of pitching moment about the quarter chord are presented graphically in this report. In addition, the data is tabulated in the appendix. Results of the aileron study show that the aileron becomes ineffective as a wind turbine aerodynamic braking device at angles of attack above 20°. Recommendations for improving effectiveness are included.
In the public domain. Prepared for NASA - Lewis Research Center under Grant NSG-3277. General Release Date: February, 1984