Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ag12-il-500000 Airfoil,ag12-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,79.6154 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-ag12-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr 0.250,0.2509,0.00481,0.00107,-0.0467,0.8066,1.0000 0.500,0.2771,0.00498,0.00105,-0.0460,0.7672,1.0000 0.750,0.3036,0.00517,0.00104,-0.0455,0.7285,1.0000 1.000,0.3303,0.00537,0.00105,-0.0451,0.6901,1.0000 1.250,0.3572,0.00557,0.00108,-0.0447,0.6523,1.0000 1.500,0.3843,0.00577,0.00112,-0.0444,0.6151,1.0000 1.750,0.4115,0.00598,0.00118,-0.0441,0.5789,1.0000 2.000,0.4387,0.00620,0.00125,-0.0439,0.5434,1.0000 2.250,0.4660,0.00642,0.00133,-0.0437,0.5089,1.0000 2.500,0.4932,0.00665,0.00143,-0.0436,0.4750,1.0000 2.750,0.5205,0.00688,0.00153,-0.0434,0.4410,1.0000 3.000,0.5477,0.00714,0.00168,-0.0432,0.4076,1.0000 3.250,0.5749,0.00739,0.00182,-0.0431,0.3753,1.0000 3.500,0.6020,0.00767,0.00198,-0.0430,0.3423,1.0000 3.750,0.6291,0.00795,0.00216,-0.0428,0.3111,1.0000 4.000,0.6561,0.00826,0.00237,-0.0427,0.2786,1.0000 4.250,0.6831,0.00858,0.00259,-0.0426,0.2484,1.0000 4.500,0.7099,0.00894,0.00284,-0.0424,0.2160,1.0000 4.750,0.7366,0.00931,0.00311,-0.0423,0.1877,1.0000 5.000,0.7632,0.00971,0.00340,-0.0421,0.1587,1.0000 5.250,0.7896,0.01013,0.00376,-0.0420,0.1323,1.0000 5.500,0.8159,0.01059,0.00412,-0.0418,0.1069,1.0000 5.750,0.8422,0.01104,0.00452,-0.0416,0.0859,1.0000 6.000,0.8682,0.01156,0.00497,-0.0413,0.0669,1.0000 6.250,0.8941,0.01209,0.00546,-0.0411,0.0510,1.0000 6.500,0.9198,0.01269,0.00601,-0.0408,0.0374,1.0000 6.750,0.9452,0.01335,0.00672,-0.0405,0.0273,1.0000 7.000,0.9703,0.01410,0.00751,-0.0400,0.0196,1.0000 7.250,0.9934,0.01541,0.00893,-0.0393,0.0140,1.0000 7.500,1.0182,0.01620,0.00983,-0.0388,0.0119,1.0000 7.750,1.0418,0.01721,0.01095,-0.0382,0.0102,1.0000 8.000,1.0604,0.01955,0.01352,-0.0370,0.0089,1.0000 8.250,1.0768,0.02265,0.01695,-0.0355,0.0085,1.0000 8.500,1.0991,0.02388,0.01837,-0.0348,0.0082,1.0000 8.750,1.1210,0.02504,0.01976,-0.0341,0.0077,1.0000 9.000,1.1412,0.02657,0.02149,-0.0333,0.0071,1.0000 9.250,1.1575,0.02900,0.02422,-0.0322,0.0069,1.0000 9.500,1.1716,0.03169,0.02723,-0.0311,0.0067,1.0000 9.750,1.1826,0.03467,0.03054,-0.0299,0.0065,1.0000 10.000,1.1899,0.03790,0.03410,-0.0287,0.0063,1.0000 10.250,1.1927,0.04138,0.03790,-0.0275,0.0061,1.0000 10.500,1.1882,0.04537,0.04219,-0.0264,0.0060,1.0000 10.750,1.1739,0.04948,0.04658,-0.0252,0.0060,1.0000 11.000,1.1506,0.05529,0.05267,-0.0273,0.0061,1.0000 11.250,1.1258,0.06410,0.06174,-0.0348,0.0063,1.0000 11.500,1.1008,0.07554,0.07339,-0.0450,0.0065,1.0000