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Cl and Cd data shown was computed by JavaFoil for a smooth airfoil at Re=6M, Mach=0.
Name Family Max Thickness (%) x-Location
of Max Thickness (%)		 Camber (%) Data
Sources		 Cl max Cl/Cd max Cd @ Cl=0.1 Cd @ Cl=0.4 Cd @ Cl=0.6
Name Family Max Thickness (%) x-Location
of Max Thickness (%)		 Camber (%) Data
Sources		 Cd @ Cl=0.1 Cd @ Cl=0.4 Cd @ Cl=0.6