Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe444-il-500000-n5 Airfoil,goe444-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,31.8173 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe444-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.5293,0.09448,0.09235,0.0027,1.0000,0.0071 -9.250,-0.6285,0.09824,0.09604,0.0041,1.0000,0.0066 -9.000,-0.6285,0.09397,0.09179,0.0021,1.0000,0.0066 -8.750,-0.6291,0.08987,0.08771,0.0002,1.0000,0.0067 -8.500,-0.6302,0.08551,0.08337,-0.0025,1.0000,0.0067 -8.250,-0.6328,0.08141,0.07930,-0.0053,1.0000,0.0068 -8.000,-0.6411,0.07620,0.07410,-0.0099,1.0000,0.0068 -7.750,-0.6429,0.07181,0.06968,-0.0122,1.0000,0.0068 -7.500,-0.6423,0.06718,0.06499,-0.0141,1.0000,0.0069 -7.250,-0.6395,0.06293,0.06065,-0.0152,1.0000,0.0070 -7.000,-0.6348,0.05888,0.05650,-0.0158,1.0000,0.0072 -6.750,-0.6282,0.05467,0.05210,-0.0160,1.0000,0.0073 -6.500,-0.6196,0.05071,0.04799,-0.0157,1.0000,0.0075 -6.250,-0.6092,0.04691,0.04402,-0.0150,1.0000,0.0078 -6.000,-0.5971,0.04324,0.04015,-0.0139,1.0000,0.0082 -5.750,-0.5832,0.03979,0.03648,-0.0125,1.0000,0.0088 -5.500,-0.5663,0.03668,0.03312,-0.0107,1.0000,0.0095 -5.250,-0.5433,0.03508,0.03123,-0.0086,1.0000,0.0104 -5.000,-0.5264,0.03252,0.02838,-0.0066,1.0000,0.0105 -4.750,-0.5095,0.02990,0.02547,-0.0046,1.0000,0.0105 -4.500,-0.4920,0.02734,0.02262,-0.0026,1.0000,0.0106 -4.250,-0.4737,0.02491,0.01989,-0.0007,1.0000,0.0106 -3.750,-0.4363,0.01721,0.01154,0.0038,1.0000,0.0058 -3.500,-0.4144,0.01519,0.00928,0.0055,1.0000,0.0053 -3.250,-0.3918,0.01357,0.00746,0.0071,1.0000,0.0049 -3.000,-0.3697,0.01222,0.00597,0.0087,1.0000,0.0046 -2.750,-0.3487,0.01109,0.00470,0.0104,1.0000,0.0043 -2.500,-0.3242,0.01013,0.00347,0.0113,0.9992,0.0039 -2.250,-0.2928,0.00939,0.00260,0.0106,0.9965,0.0037 -2.000,-0.2608,0.00892,0.00200,0.0097,0.9935,0.0035 -1.750,-0.2277,0.00866,0.00163,0.0085,0.9897,0.0034 -1.500,-0.1925,0.00847,0.00136,0.0067,0.9858,0.0035 -1.250,-0.1592,0.00832,0.00117,0.0055,0.9798,0.0038 -1.000,-0.1259,0.00820,0.00104,0.0041,0.9740,0.0048 -0.750,-0.1009,0.00657,0.00089,0.0037,0.9664,0.4085 -0.500,-0.0882,0.00483,0.00100,0.0071,0.9554,0.8661 -0.250,-0.0447,0.00478,0.00109,0.0038,0.9499,0.9250 0.000,-0.0002,0.00478,0.00110,0.0000,0.9402,0.9400 0.250,0.0448,0.00478,0.00109,-0.0038,0.9247,0.9499 0.500,0.0883,0.00483,0.00100,-0.0071,0.8657,0.9554 0.750,0.1015,0.00649,0.00088,-0.0037,0.4274,0.9664 1.000,0.1258,0.00820,0.00105,-0.0041,0.0050,0.9739 1.250,0.1590,0.00832,0.00117,-0.0054,0.0039,0.9797 1.500,0.1924,0.00847,0.00136,-0.0067,0.0035,0.9856 1.750,0.2275,0.00865,0.00161,-0.0084,0.0035,0.9896 2.000,0.2606,0.00893,0.00201,-0.0096,0.0035,0.9933 2.250,0.2926,0.00937,0.00258,-0.0105,0.0037,0.9963 2.500,0.3239,0.01018,0.00352,-0.0112,0.0040,0.9990 2.750,0.3492,0.01112,0.00473,-0.0105,0.0043,1.0000 3.000,0.3704,0.01223,0.00598,-0.0088,0.0046,1.0000 3.250,0.3925,0.01358,0.00747,-0.0072,0.0049,1.0000 3.500,0.4150,0.01522,0.00931,-0.0056,0.0053,1.0000 3.750,0.4370,0.01709,0.01142,-0.0040,0.0057,1.0000 4.000,0.4550,0.02260,0.01731,-0.0013,0.0106,1.0000 4.250,0.4742,0.02489,0.01988,0.0006,0.0106,1.0000 4.500,0.4923,0.02743,0.02271,0.0026,0.0106,1.0000 4.750,0.5097,0.02994,0.02551,0.0046,0.0105,1.0000 5.000,0.5267,0.03249,0.02835,0.0066,0.0105,1.0000 5.250,0.5435,0.03505,0.03120,0.0086,0.0104,1.0000 5.500,0.5670,0.03661,0.03305,0.0107,0.0094,1.0000 5.750,0.5833,0.03974,0.03643,0.0125,0.0087,1.0000 6.000,0.5970,0.04324,0.04015,0.0139,0.0082,1.0000 6.250,0.6089,0.04699,0.04410,0.0150,0.0079,1.0000 6.500,0.6194,0.05064,0.04792,0.0157,0.0075,1.0000 6.750,0.6279,0.05463,0.05207,0.0160,0.0073,1.0000 7.000,0.6345,0.05874,0.05636,0.0159,0.0071,1.0000 7.250,0.6392,0.06278,0.06050,0.0154,0.0070,1.0000 7.500,0.6415,0.06727,0.06507,0.0142,0.0069,1.0000 7.750,0.6425,0.07162,0.06948,0.0124,0.0068,1.0000 8.000,0.6407,0.07603,0.07393,0.0102,0.0067,1.0000 8.250,0.6330,0.08100,0.07889,0.0059,0.0068,1.0000