Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe444-il-500000 Airfoil,goe444-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,45.9266 Max Cl/Cd alpha,1.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe444-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.6406,0.08071,0.07851,-0.0074,1.0000,0.0087 -8.250,-0.6485,0.07538,0.07318,-0.0124,1.0000,0.0086 -8.000,-0.6530,0.07063,0.06839,-0.0145,1.0000,0.0086 -7.750,-0.6539,0.06613,0.06381,-0.0159,1.0000,0.0087 -7.500,-0.6529,0.06180,0.05939,-0.0166,1.0000,0.0088 -7.250,-0.6498,0.05771,0.05519,-0.0168,1.0000,0.0089 -7.000,-0.6445,0.05380,0.05115,-0.0166,1.0000,0.0091 -6.750,-0.6371,0.05003,0.04723,-0.0161,1.0000,0.0093 -6.500,-0.6282,0.04643,0.04347,-0.0153,1.0000,0.0097 -6.250,-0.6176,0.04295,0.03981,-0.0141,1.0000,0.0101 -6.000,-0.6053,0.03963,0.03627,-0.0127,1.0000,0.0106 -5.750,-0.5918,0.03641,0.03283,-0.0111,1.0000,0.0112 -5.500,-0.5767,0.03338,0.02954,-0.0093,1.0000,0.0120 -5.250,-0.5600,0.03060,0.02649,-0.0073,1.0000,0.0131 -5.000,-0.5359,0.02967,0.02534,-0.0055,1.0000,0.0158 -4.750,-0.5142,0.02880,0.02420,-0.0036,1.0000,0.0165 -4.500,-0.4965,0.02629,0.02139,-0.0015,1.0000,0.0165 -4.000,-0.4398,0.00823,0.00294,0.0005,1.0000,0.0165 -3.750,-0.4410,0.01606,0.01004,0.0051,1.0000,0.0177 -3.250,-0.3953,0.01305,0.00680,0.0080,1.0000,0.0154 -3.000,-0.3742,0.01163,0.00529,0.0097,1.0000,0.0150 -2.750,-0.3538,0.01060,0.00417,0.0114,1.0000,0.0151 -2.500,-0.3326,0.00990,0.00339,0.0130,1.0000,0.0161 -2.250,-0.3121,0.00908,0.00243,0.0146,1.0000,0.0200 -2.000,-0.2897,0.00875,0.00206,0.0157,1.0000,0.0271 -1.750,-0.2768,0.00690,0.00155,0.0180,1.0000,0.3958 -1.500,-0.2636,0.00595,0.00151,0.0207,1.0000,0.6330 -1.250,-0.2516,0.00539,0.00160,0.0242,1.0000,0.7955 -1.000,-0.1676,0.00522,0.00186,0.0130,1.0000,0.9679 -0.750,-0.1221,0.00532,0.00190,0.0091,1.0000,0.9817 -0.500,-0.0699,0.00541,0.00194,0.0037,1.0000,0.9925 -0.250,-0.0194,0.00545,0.00195,-0.0014,1.0000,0.9991 0.000,0.0000,0.00544,0.00193,0.0000,1.0000,1.0000 0.250,0.0197,0.00545,0.00195,0.0013,0.9991,1.0000 0.500,0.0698,0.00541,0.00194,-0.0037,0.9925,1.0000 0.750,0.1215,0.00532,0.00190,-0.0089,0.9819,1.0000 1.000,0.1672,0.00522,0.00186,-0.0129,0.9682,1.0000 1.250,0.2503,0.00545,0.00157,-0.0239,0.7766,1.0000 1.500,0.2637,0.00594,0.00151,-0.0207,0.6340,1.0000 2.000,0.2897,0.00874,0.00205,-0.0158,0.0269,1.0000 2.250,0.3120,0.00909,0.00244,-0.0146,0.0197,1.0000 2.500,0.3327,0.00988,0.00337,-0.0130,0.0160,1.0000 2.750,0.3537,0.01059,0.00416,-0.0114,0.0152,1.0000 3.000,0.3742,0.01163,0.00529,-0.0097,0.0150,1.0000 3.250,0.3953,0.01306,0.00681,-0.0080,0.0154,1.0000 5.000,0.5065,0.01758,0.01352,0.0078,0.0163,1.0000 5.250,0.5331,0.01727,0.01341,0.0095,0.0137,1.0000 5.500,0.5486,0.01991,0.01633,0.0114,0.0125,1.0000 5.750,0.5622,0.02305,0.01972,0.0132,0.0116,1.0000 6.000,0.5742,0.02650,0.02340,0.0146,0.0110,1.0000 6.250,0.5845,0.03029,0.02740,0.0159,0.0104,1.0000 6.500,0.5930,0.03433,0.03163,0.0168,0.0101,1.0000 6.750,0.5990,0.03868,0.03614,0.0175,0.0098,1.0000 7.000,0.6028,0.04316,0.04076,0.0178,0.0095,1.0000 7.250,0.6038,0.04782,0.04554,0.0177,0.0094,1.0000 7.500,0.6009,0.05272,0.05054,0.0172,0.0093,1.0000 7.750,0.5941,0.05786,0.05575,0.0158,0.0093,1.0000 8.000,0.5766,0.06295,0.06089,0.0134,0.0095,1.0000 8.250,0.5619,0.06881,0.06672,0.0086,0.0096,1.0000 8.500,0.5545,0.07399,0.07188,0.0060,0.0096,1.0000 8.750,0.5492,0.07904,0.07692,0.0038,0.0096,1.0000 9.000,0.5454,0.08391,0.08177,0.0020,0.0096,1.0000