Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe444-il-50000-n5 Airfoil,goe444-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,16.4649 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe444-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.6463,0.10472,0.09810,0.0068,1.0000,0.1220 -8.500,-0.6538,0.10095,0.09445,0.0040,1.0000,0.1291 -8.000,-0.6621,0.09343,0.08708,0.0002,1.0000,0.1426 -7.500,-0.6491,0.07981,0.07327,-0.0102,1.0000,0.0671 -7.250,-0.6445,0.07382,0.06715,-0.0127,1.0000,0.0495 -7.000,-0.6376,0.06907,0.06224,-0.0137,1.0000,0.0416 -6.750,-0.6327,0.06425,0.05719,-0.0147,1.0000,0.0381 -6.500,-0.6228,0.06003,0.05266,-0.0147,1.0000,0.0343 -6.250,-0.6129,0.05586,0.04828,-0.0144,1.0000,0.0327 -6.000,-0.6011,0.05176,0.04386,-0.0139,1.0000,0.0310 -5.750,-0.5871,0.04777,0.03942,-0.0130,1.0000,0.0294 -5.500,-0.5705,0.04414,0.03524,-0.0117,1.0000,0.0283 -5.250,-0.5529,0.04085,0.03142,-0.0105,1.0000,0.0283 -5.000,-0.5343,0.03775,0.02793,-0.0093,1.0000,0.0297 -4.750,-0.5132,0.03490,0.02461,-0.0080,1.0000,0.0306 -4.500,-0.4901,0.03220,0.02143,-0.0066,1.0000,0.0309 -4.250,-0.4652,0.02964,0.01844,-0.0053,1.0000,0.0311 -4.000,-0.4392,0.02733,0.01576,-0.0040,1.0000,0.0318 -3.750,-0.4128,0.02538,0.01349,-0.0026,1.0000,0.0344 -3.500,-0.3885,0.02360,0.01149,-0.0014,1.0000,0.0399 -3.250,-0.3642,0.02217,0.00975,0.0000,1.0000,0.0448 -3.000,-0.3404,0.02073,0.00808,0.0010,1.0000,0.0581 -2.750,-0.2030,0.01596,0.00620,-0.0150,1.0000,1.0000 -2.500,-0.1856,0.01564,0.00554,-0.0138,1.0000,1.0000 -2.250,-0.1678,0.01537,0.00496,-0.0125,1.0000,1.0000 -2.000,-0.1498,0.01515,0.00447,-0.0112,1.0000,1.0000 -1.750,-0.1314,0.01497,0.00405,-0.0098,1.0000,1.0000 -1.500,-0.1128,0.01482,0.00364,-0.0085,1.0000,1.0000 -1.250,-0.0942,0.01469,0.00335,-0.0071,1.0000,1.0000 -1.000,-0.0754,0.01460,0.00313,-0.0057,1.0000,1.0000 -0.750,-0.0565,0.01452,0.00296,-0.0043,1.0000,1.0000 -0.500,-0.0377,0.01447,0.00282,-0.0029,1.0000,1.0000 -0.250,-0.0188,0.01444,0.00274,-0.0015,1.0000,1.0000 0.000,0.0000,0.01443,0.00272,0.0000,1.0000,1.0000 0.250,0.0188,0.01444,0.00274,0.0015,1.0000,1.0000 0.500,0.0377,0.01447,0.00282,0.0029,1.0000,1.0000 0.750,0.0565,0.01452,0.00296,0.0043,1.0000,1.0000 1.000,0.0753,0.01460,0.00313,0.0057,1.0000,1.0000 1.250,0.0941,0.01470,0.00335,0.0071,1.0000,1.0000 1.500,0.1127,0.01482,0.00363,0.0085,1.0000,1.0000 1.750,0.1313,0.01497,0.00406,0.0099,1.0000,1.0000 2.000,0.1496,0.01516,0.00446,0.0112,1.0000,1.0000 2.250,0.1676,0.01538,0.00496,0.0125,1.0000,1.0000 2.500,0.1853,0.01565,0.00553,0.0138,1.0000,1.0000 2.750,0.2027,0.01597,0.00621,0.0151,1.0000,1.0000 3.000,0.3409,0.02074,0.00811,-0.0011,0.0578,1.0000 3.250,0.3646,0.02216,0.00974,-0.0001,0.0449,1.0000 3.500,0.3889,0.02362,0.01151,0.0013,0.0399,1.0000 3.750,0.4133,0.02539,0.01352,0.0025,0.0342,1.0000 4.000,0.4395,0.02733,0.01577,0.0039,0.0319,1.0000 4.250,0.4655,0.02962,0.01841,0.0052,0.0312,1.0000 4.500,0.4904,0.03217,0.02141,0.0065,0.0310,1.0000 4.750,0.5135,0.03493,0.02465,0.0079,0.0306,1.0000 5.000,0.5343,0.03778,0.02796,0.0093,0.0295,1.0000 5.250,0.5528,0.04085,0.03142,0.0104,0.0283,1.0000 5.500,0.5702,0.04416,0.03523,0.0117,0.0281,1.0000 5.750,0.5869,0.04775,0.03940,0.0130,0.0293,1.0000 6.000,0.6009,0.05177,0.04387,0.0139,0.0310,1.0000 6.250,0.6126,0.05582,0.04825,0.0145,0.0327,1.0000 6.500,0.6224,0.06000,0.05263,0.0148,0.0343,1.0000 6.750,0.6324,0.06414,0.05708,0.0148,0.0380,1.0000 7.000,0.6372,0.06902,0.06220,0.0138,0.0416,1.0000 7.250,0.6438,0.07385,0.06719,0.0128,0.0497,1.0000 7.750,0.5719,0.07062,0.06448,0.0144,0.0479,1.0000 8.000,0.5579,0.07532,0.06916,0.0115,0.0491,1.0000 8.250,0.5476,0.08056,0.07434,0.0076,0.0510,1.0000 8.500,0.5434,0.08555,0.07928,0.0056,0.0549,1.0000 9.000,0.6466,0.10842,0.10174,-0.0081,0.1171,1.0000 9.500,0.6476,0.11632,0.10952,-0.0111,0.1089,1.0000 9.750,0.6476,0.11992,0.11307,-0.0128,0.1040,1.0000 10.000,0.6578,0.12442,0.11759,-0.0122,0.1003,1.0000 10.250,0.6641,0.12953,0.12265,-0.0125,0.0981,1.0000 10.500,0.6531,0.13165,0.12466,-0.0172,0.0941,1.0000