Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ag12-il-1000000 Airfoil,ag12-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,92.6316 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-ag12-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.5958,0.11439,0.11280,0.0270,1.0000,0.0069 -9.250,-0.5916,0.11061,0.10903,0.0254,1.0000,0.0070 -9.000,-0.5876,0.10678,0.10522,0.0236,1.0000,0.0071 -5.750,-0.4270,0.01934,0.01584,-0.0456,1.0000,0.0060 -5.250,-0.3739,0.01437,0.01013,-0.0458,1.0000,0.0059 -5.000,-0.3476,0.01174,0.00716,-0.0459,1.0000,0.0069 -4.750,-0.3206,0.01114,0.00649,-0.0457,1.0000,0.0075 -4.500,-0.2936,0.01043,0.00569,-0.0455,1.0000,0.0079 -4.250,-0.2666,0.00969,0.00485,-0.0452,1.0000,0.0083 -4.000,-0.2396,0.00912,0.00420,-0.0449,1.0000,0.0088 -3.750,-0.2129,0.00876,0.00380,-0.0446,1.0000,0.0095 -3.500,-0.1861,0.00828,0.00325,-0.0442,1.0000,0.0098 -3.250,-0.1584,0.00735,0.00214,-0.0439,1.0000,0.0125 -3.000,-0.1318,0.00709,0.00186,-0.0436,1.0000,0.0161 -2.750,-0.1044,0.00668,0.00152,-0.0433,0.9999,0.0362 -2.500,-0.0672,0.00634,0.00132,-0.0454,0.9951,0.0743 -2.250,-0.0316,0.00602,0.00116,-0.0472,0.9868,0.1201 -2.000,0.0040,0.00568,0.00104,-0.0489,0.9739,0.1835 -1.750,0.0371,0.00540,0.00093,-0.0500,0.9515,0.2457 -1.500,0.0641,0.00523,0.00084,-0.0496,0.9172,0.3028 -1.250,0.0892,0.00514,0.00078,-0.0487,0.8786,0.3562 -1.000,0.1150,0.00511,0.00074,-0.0480,0.8400,0.4052 -0.750,0.1413,0.00506,0.00071,-0.0476,0.8021,0.4627 -0.500,0.1680,0.00503,0.00069,-0.0472,0.7643,0.5222 -0.250,0.1949,0.00495,0.00069,-0.0469,0.7270,0.5954 0.000,0.2216,0.00484,0.00070,-0.0466,0.6916,0.6823 0.250,0.2458,0.00450,0.00073,-0.0457,0.6576,0.8355 0.500,0.2725,0.00433,0.00070,-0.0450,0.6229,1.0000 0.750,0.3003,0.00449,0.00072,-0.0449,0.5885,1.0000 1.000,0.3280,0.00466,0.00074,-0.0448,0.5559,1.0000 1.250,0.3558,0.00482,0.00077,-0.0447,0.5241,1.0000 1.500,0.3836,0.00499,0.00081,-0.0446,0.4928,1.0000 1.750,0.4113,0.00517,0.00087,-0.0445,0.4620,1.0000 2.000,0.4390,0.00536,0.00093,-0.0444,0.4325,1.0000 2.250,0.4667,0.00554,0.00100,-0.0444,0.4031,1.0000 2.500,0.4944,0.00574,0.00109,-0.0443,0.3733,1.0000 2.750,0.5220,0.00594,0.00120,-0.0442,0.3453,1.0000 3.000,0.5496,0.00616,0.00130,-0.0441,0.3160,1.0000 3.250,0.5771,0.00638,0.00142,-0.0441,0.2897,1.0000 3.500,0.6045,0.00662,0.00156,-0.0440,0.2603,1.0000 3.750,0.6319,0.00686,0.00170,-0.0439,0.2353,1.0000 4.000,0.6592,0.00714,0.00189,-0.0438,0.2066,1.0000 4.250,0.6864,0.00741,0.00207,-0.0437,0.1832,1.0000 4.500,0.7135,0.00771,0.00227,-0.0436,0.1577,1.0000 5.000,0.7675,0.00836,0.00274,-0.0433,0.1113,1.0000 5.250,0.7943,0.00869,0.00301,-0.0432,0.0929,1.0000 5.500,0.8211,0.00904,0.00329,-0.0430,0.0750,1.0000 5.750,0.8476,0.00945,0.00361,-0.0429,0.0577,1.0000 6.000,0.8742,0.00984,0.00395,-0.0427,0.0439,1.0000 6.250,0.9006,0.01024,0.00431,-0.0425,0.0326,1.0000 6.500,0.9268,0.01070,0.00475,-0.0423,0.0229,1.0000 6.750,0.9531,0.01112,0.00515,-0.0421,0.0174,1.0000 7.000,0.9791,0.01161,0.00568,-0.0418,0.0124,1.0000 7.250,1.0042,0.01243,0.00656,-0.0413,0.0082,1.0000 7.500,1.0299,0.01294,0.00713,-0.0410,0.0069,1.0000 7.750,1.0547,0.01371,0.00797,-0.0405,0.0056,1.0000 8.000,1.0771,0.01511,0.00960,-0.0397,0.0048,1.0000 8.250,1.1018,0.01578,0.01035,-0.0393,0.0046,1.0000 8.500,1.1254,0.01670,0.01142,-0.0387,0.0044,1.0000 8.750,1.1483,0.01772,0.01259,-0.0381,0.0042,1.0000 9.000,1.1706,0.01884,0.01385,-0.0375,0.0040,1.0000 9.250,1.1923,0.02001,0.01517,-0.0368,0.0038,1.0000 9.500,1.2136,0.02119,0.01649,-0.0361,0.0036,1.0000 9.750,1.2346,0.02233,0.01777,-0.0354,0.0034,1.0000 10.000,1.2551,0.02347,0.01903,-0.0348,0.0032,1.0000 10.250,1.2733,0.02496,0.02067,-0.0340,0.0030,1.0000 10.500,1.2782,0.02885,0.02495,-0.0322,0.0027,1.0000 11.000,1.2619,0.03906,0.03611,-0.0282,0.0025,1.0000 11.250,1.2563,0.04221,0.03948,-0.0267,0.0025,1.0000 11.500,1.2402,0.04627,0.04375,-0.0264,0.0025,1.0000 11.750,1.2242,0.05214,0.04983,-0.0304,0.0025,1.0000