Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe444-il-100000-n5 Airfoil,goe444-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,24.7894 Max Cl/Cd alpha,2.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe444-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6377,0.08864,0.08396,-0.0038,1.0000,0.0386 -8.000,-0.6413,0.08433,0.07968,-0.0069,1.0000,0.0390 -7.750,-0.6433,0.08010,0.07545,-0.0091,1.0000,0.0396 -7.500,-0.6429,0.07578,0.07109,-0.0112,1.0000,0.0405 -7.250,-0.6412,0.07137,0.06661,-0.0131,1.0000,0.0416 -7.000,-0.6408,0.06881,0.06354,-0.0161,1.0000,0.0458 -6.500,-0.5796,0.04500,0.04029,-0.0169,1.0000,0.0521 -6.000,-0.5977,0.04874,0.04286,-0.0142,1.0000,0.0251 -5.750,-0.5849,0.04482,0.03867,-0.0132,1.0000,0.0237 -5.500,-0.5698,0.04095,0.03438,-0.0119,1.0000,0.0216 -5.250,-0.5465,0.03843,0.03112,-0.0094,1.0000,0.0182 -5.000,-0.5300,0.03470,0.02709,-0.0080,1.0000,0.0174 -4.750,-0.5121,0.03140,0.02342,-0.0065,1.0000,0.0167 -4.500,-0.4917,0.02858,0.02018,-0.0049,1.0000,0.0161 -4.250,-0.4695,0.02601,0.01718,-0.0033,1.0000,0.0157 -4.000,-0.4458,0.02365,0.01444,-0.0017,1.0000,0.0156 -3.750,-0.4213,0.02151,0.01199,-0.0003,1.0000,0.0159 -3.500,-0.3972,0.01980,0.01005,0.0011,1.0000,0.0170 -3.250,-0.3758,0.01812,0.00823,0.0027,1.0000,0.0195 -3.000,-0.3554,0.01680,0.00682,0.0043,1.0000,0.0216 -2.750,-0.3341,0.01579,0.00559,0.0059,1.0000,0.0255 -2.500,-0.3122,0.01489,0.00456,0.0074,1.0000,0.0365 -2.250,-0.2996,0.01205,0.00357,0.0095,1.0000,0.4212 -2.000,-0.2037,0.01110,0.00393,-0.0006,1.0000,0.9679 -1.750,-0.1549,0.01102,0.00351,-0.0052,1.0000,0.9856 -1.500,-0.1088,0.01090,0.00308,-0.0095,1.0000,0.9993 -1.250,-0.0896,0.01077,0.00283,-0.0082,1.0000,1.0000 -1.000,-0.0721,0.01066,0.00264,-0.0066,1.0000,1.0000 -0.750,-0.0543,0.01058,0.00249,-0.0049,1.0000,1.0000 -0.500,-0.0364,0.01053,0.00237,-0.0033,1.0000,1.0000 -0.250,-0.0183,0.01049,0.00231,-0.0016,1.0000,1.0000 0.000,0.0000,0.01048,0.00229,0.0000,1.0000,1.0000 0.250,0.0183,0.01050,0.00231,0.0016,1.0000,1.0000 0.500,0.0364,0.01053,0.00238,0.0033,1.0000,1.0000 0.750,0.0543,0.01058,0.00249,0.0049,1.0000,1.0000 1.000,0.0720,0.01066,0.00264,0.0066,1.0000,1.0000 1.250,0.0895,0.01077,0.00283,0.0083,1.0000,1.0000 1.500,0.1088,0.01090,0.00308,0.0095,0.9992,1.0000 1.750,0.1551,0.01103,0.00353,0.0052,0.9854,1.0000 2.000,0.2036,0.01110,0.00393,0.0006,0.9678,1.0000 2.250,0.3002,0.01211,0.00358,-0.0096,0.4107,1.0000 2.500,0.3129,0.01493,0.00459,-0.0075,0.0361,1.0000 2.750,0.3349,0.01581,0.00562,-0.0061,0.0249,1.0000 3.000,0.3561,0.01683,0.00685,-0.0045,0.0215,1.0000 3.250,0.3765,0.01812,0.00823,-0.0028,0.0195,1.0000 3.500,0.3979,0.01981,0.01006,-0.0013,0.0169,1.0000 3.750,0.4220,0.02154,0.01203,0.0001,0.0159,1.0000 4.000,0.4464,0.02365,0.01444,0.0016,0.0157,1.0000 4.250,0.4699,0.02596,0.01714,0.0031,0.0158,1.0000 4.500,0.4921,0.02854,0.02014,0.0048,0.0161,1.0000 4.750,0.5124,0.03143,0.02345,0.0064,0.0167,1.0000 5.000,0.5303,0.03474,0.02714,0.0080,0.0174,1.0000 5.250,0.5468,0.03838,0.03107,0.0093,0.0182,1.0000 5.750,0.5505,0.02958,0.02391,0.0149,0.0237,1.0000 6.000,0.5601,0.03387,0.02843,0.0159,0.0255,1.0000 7.000,0.6370,0.06705,0.06213,0.0149,0.0435,1.0000 7.500,0.6425,0.07568,0.07100,0.0114,0.0406,1.0000 7.750,0.6429,0.08000,0.07535,0.0093,0.0396,1.0000 8.000,0.6408,0.08427,0.07963,0.0070,0.0391,1.0000 8.250,0.6373,0.08860,0.08390,0.0040,0.0386,1.0000