Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-s2062-il-500000 Airfoil,s2062-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,89.261 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-s2062-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr 0.250,0.2560,0.00524,0.00164,-0.0536,0.8604,0.9464 0.500,0.2885,0.00523,0.00159,-0.0543,0.8471,0.9660 0.750,0.3257,0.00523,0.00155,-0.0561,0.8329,0.9815 1.000,0.3655,0.00524,0.00150,-0.0586,0.8171,0.9929 1.250,0.3993,0.00527,0.00147,-0.0598,0.7984,1.0000 1.500,0.4221,0.00534,0.00146,-0.0587,0.7771,1.0000 1.750,0.4457,0.00543,0.00147,-0.0577,0.7537,1.0000 2.000,0.4698,0.00555,0.00151,-0.0568,0.7269,1.0000 2.250,0.4942,0.00570,0.00155,-0.0560,0.6969,1.0000 2.500,0.5188,0.00589,0.00161,-0.0553,0.6646,1.0000 2.750,0.5433,0.00610,0.00169,-0.0545,0.6295,1.0000 3.000,0.5677,0.00636,0.00179,-0.0538,0.5894,1.0000 3.250,0.5907,0.00674,0.00194,-0.0528,0.5282,1.0000 3.500,0.6135,0.00719,0.00211,-0.0519,0.4617,1.0000 3.750,0.6378,0.00757,0.00230,-0.0513,0.4116,1.0000 4.000,0.6612,0.00807,0.00252,-0.0506,0.3503,1.0000 4.250,0.6841,0.00866,0.00281,-0.0499,0.2787,1.0000 4.500,0.7082,0.00915,0.00308,-0.0494,0.2283,1.0000 4.750,0.7319,0.00970,0.00340,-0.0489,0.1756,1.0000 5.000,0.7549,0.01037,0.00379,-0.0483,0.1180,1.0000 5.250,0.7752,0.01147,0.00444,-0.0472,0.0394,1.0000 5.500,0.7991,0.01210,0.00502,-0.0465,0.0254,1.0000 5.750,0.8230,0.01273,0.00569,-0.0458,0.0214,1.0000 6.000,0.8466,0.01339,0.00644,-0.0450,0.0201,1.0000 6.250,0.8703,0.01400,0.00714,-0.0442,0.0194,1.0000 6.500,0.8932,0.01471,0.00796,-0.0434,0.0186,1.0000 6.750,0.9154,0.01554,0.00887,-0.0424,0.0179,1.0000 7.000,0.9370,0.01647,0.00989,-0.0413,0.0172,1.0000 7.250,0.9589,0.01735,0.01083,-0.0404,0.0163,1.0000 7.500,0.9799,0.01839,0.01194,-0.0394,0.0154,1.0000 7.750,0.9999,0.01983,0.01348,-0.0382,0.0150,1.0000 8.000,1.0194,0.02177,0.01558,-0.0370,0.0146,1.0000 8.250,1.0386,0.02433,0.01834,-0.0357,0.0143,1.0000 8.500,1.0566,0.02734,0.02163,-0.0344,0.0142,1.0000 8.750,1.0690,0.03142,0.02611,-0.0325,0.0140,1.0000 9.000,1.0917,0.03043,0.02526,-0.0316,0.0131,1.0000