Wind-tunnel tests have been conducted at Mach numbers from 0.60 to 0.81 to determine the effects of trailing-edge geometry on the aerodynamic characteristics of a NASA supercritical airfoil shape. Variations in trailing-edge thicknesses from 0 to 1.5 percent of the chord and a cavity in the trailing edge were investigated with airfoils with maximum thicknesses of 10 and 11 percent of the chord.
Wind-tunnel investigation of effects of trailing-edge geometry on a NASA supercritical airfoil section
1971-09-01
Report
No indication
English
Wind Tunnel Test on Wind Turbine Airfoil with Adaptive Trailing Edge Geometry AIAA Paper
British Library Conference Proceedings | 2007
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