Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe443-il-200000-n5 Airfoil,goe443-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,32.1688 Max Cl/Cd alpha,1.75 Url,http://www.airfoiltools.com/polar/csv?polar=xf-goe443-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6428,0.09051,0.08711,0.0075,1.0000,0.0157 -8.000,-0.6444,0.08626,0.08290,0.0047,1.0000,0.0158 -7.750,-0.6479,0.08196,0.07864,0.0012,1.0000,0.0157 -7.500,-0.6471,0.07724,0.07391,-0.0027,1.0000,0.0158 -7.250,-0.6438,0.07238,0.06899,-0.0060,1.0000,0.0161 -7.000,-0.6379,0.06769,0.06422,-0.0086,1.0000,0.0163 -6.750,-0.6297,0.06299,0.05940,-0.0106,1.0000,0.0169 -6.250,-0.5967,0.05565,0.05145,-0.0124,1.0000,0.0190 -5.750,-0.5680,0.04805,0.04334,-0.0117,1.0000,0.0191 -5.250,-0.5418,0.03666,0.03155,-0.0102,1.0000,0.0088 -5.000,-0.5243,0.03273,0.02726,-0.0090,1.0000,0.0081 -4.750,-0.5044,0.02908,0.02321,-0.0075,1.0000,0.0074 -4.500,-0.4828,0.02555,0.01922,-0.0058,1.0000,0.0068 -4.250,-0.4598,0.02230,0.01547,-0.0039,1.0000,0.0065 -4.000,-0.4363,0.01995,0.01273,-0.0026,1.0000,0.0067 -3.750,-0.4120,0.01881,0.01135,-0.0016,1.0000,0.0090 -3.500,-0.3877,0.01693,0.00914,-0.0003,1.0000,0.0094 -3.250,-0.3640,0.01529,0.00729,0.0010,1.0000,0.0098 -3.000,-0.3426,0.01352,0.00538,0.0027,1.0000,0.0107 -2.750,-0.3208,0.01243,0.00420,0.0039,1.0000,0.0149 -2.500,-0.2977,0.01168,0.00327,0.0051,1.0000,0.0192 -2.250,-0.2750,0.01090,0.00251,0.0061,1.0000,0.0536 -2.000,-0.2622,0.00867,0.00204,0.0079,1.0000,0.4695 -1.750,-0.2474,0.00770,0.00191,0.0108,1.0000,0.6852 -1.500,-0.2257,0.00721,0.00192,0.0131,1.0000,0.8454 -1.250,-0.1447,0.00731,0.00192,0.0026,1.0000,0.9724 -1.000,-0.1018,0.00730,0.00178,-0.0009,1.0000,0.9880 -0.750,-0.0626,0.00726,0.00166,-0.0036,1.0000,0.9982 -0.500,-0.0392,0.00723,0.00156,-0.0030,1.0000,1.0000 -0.250,-0.0197,0.00720,0.00151,-0.0015,1.0000,1.0000 0.000,0.0000,0.00719,0.00149,0.0000,1.0000,1.0000 0.250,0.0197,0.00720,0.00151,0.0015,1.0000,1.0000 0.500,0.0392,0.00723,0.00156,0.0030,1.0000,1.0000 0.750,0.0627,0.00727,0.00166,0.0036,0.9981,1.0000 1.000,0.1019,0.00730,0.00179,0.0008,0.9880,1.0000 1.250,0.1460,0.00731,0.00192,-0.0029,0.9716,1.0000 1.500,0.2258,0.00721,0.00192,-0.0132,0.8462,1.0000 1.750,0.2477,0.00770,0.00192,-0.0109,0.6856,1.0000 2.000,0.2622,0.00869,0.00204,-0.0079,0.4647,1.0000 2.250,0.2752,0.01090,0.00251,-0.0062,0.0535,1.0000 2.500,0.2980,0.01167,0.00326,-0.0051,0.0193,1.0000 2.750,0.3211,0.01242,0.00419,-0.0040,0.0143,1.0000 3.000,0.3428,0.01350,0.00536,-0.0027,0.0107,1.0000 3.250,0.3641,0.01529,0.00729,-0.0011,0.0099,1.0000 3.500,0.3878,0.01694,0.00916,0.0003,0.0094,1.0000 3.750,0.4123,0.01869,0.01123,0.0016,0.0086,1.0000 4.000,0.4365,0.02001,0.01281,0.0026,0.0068,1.0000 4.250,0.4599,0.02230,0.01547,0.0039,0.0065,1.0000 4.500,0.4828,0.02557,0.01924,0.0058,0.0069,1.0000 4.750,0.5044,0.02906,0.02318,0.0075,0.0074,1.0000 5.000,0.5243,0.03273,0.02726,0.0090,0.0081,1.0000 5.250,0.5417,0.03663,0.03152,0.0102,0.0089,1.0000 5.750,0.5678,0.04803,0.04332,0.0118,0.0191,1.0000 6.250,0.5964,0.05562,0.05142,0.0125,0.0190,1.0000 6.500,0.6098,0.05939,0.05547,0.0123,0.0188,1.0000 6.750,0.6290,0.06299,0.05939,0.0107,0.0171,1.0000 7.000,0.6376,0.06760,0.06413,0.0087,0.0164,1.0000 7.250,0.6433,0.07239,0.06900,0.0061,0.0161,1.0000 7.500,0.6469,0.07714,0.07381,0.0028,0.0159,1.0000 7.750,0.6477,0.08193,0.07861,-0.0011,0.0158,1.0000 8.000,0.6441,0.08627,0.08290,-0.0047,0.0158,1.0000 8.250,0.6427,0.09049,0.08708,-0.0075,0.0155,1.0000