Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe444-il-1000000 Airfoil,goe444-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,42.267 Max Cl/Cd alpha,2.75 Url,http://airfoiltools.com/polar/csv?polar=xf-goe444-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.6379,0.08310,0.08151,-0.0025,1.0000,0.0059 -8.250,-0.6440,0.07810,0.07654,-0.0071,1.0000,0.0057 -8.000,-0.6524,0.07317,0.07159,-0.0110,1.0000,0.0058 -7.750,-0.6541,0.06811,0.06647,-0.0138,1.0000,0.0057 -7.500,-0.6529,0.06325,0.06154,-0.0155,1.0000,0.0058 -7.250,-0.6492,0.05858,0.05676,-0.0164,1.0000,0.0060 -7.000,-0.6429,0.05419,0.05225,-0.0165,1.0000,0.0062 -6.750,-0.6335,0.05019,0.04811,-0.0159,1.0000,0.0065 -6.500,-0.6158,0.04758,0.04538,-0.0149,1.0000,0.0072 -6.250,-0.6014,0.04465,0.04230,-0.0137,1.0000,0.0074 -6.000,-0.5891,0.04135,0.03882,-0.0122,1.0000,0.0075 -5.750,-0.5765,0.03799,0.03527,-0.0105,1.0000,0.0075 -5.500,-0.5632,0.03478,0.03184,-0.0085,1.0000,0.0076 -5.250,-0.5490,0.03171,0.02854,-0.0064,1.0000,0.0076 -5.000,-0.5343,0.02871,0.02530,-0.0042,1.0000,0.0076 -4.750,-0.5187,0.02584,0.02217,-0.0019,1.0000,0.0076 -4.500,-0.5025,0.02305,0.01911,0.0005,1.0000,0.0076 -4.250,-0.4944,0.01549,0.01080,0.0052,1.0000,0.0054 -4.000,-0.4733,0.01324,0.00829,0.0073,1.0000,0.0058 -3.750,-0.4501,0.01285,0.00783,0.0084,1.0000,0.0071 -3.500,-0.4294,0.01132,0.00610,0.0100,1.0000,0.0086 -3.250,-0.4085,0.01043,0.00518,0.0113,1.0000,0.0104 -3.000,-0.3881,0.00941,0.00405,0.0131,1.0000,0.0098 -2.750,-0.3673,0.00871,0.00326,0.0147,1.0000,0.0093 -2.500,-0.3408,0.00806,0.00250,0.0151,0.9993,0.0097 -2.250,-0.3051,0.00757,0.00191,0.0134,0.9971,0.0135 -2.000,-0.2682,0.00735,0.00164,0.0113,0.9948,0.0162 -1.750,-0.2385,0.00627,0.00123,0.0104,0.9918,0.2180 -1.500,-0.2081,0.00552,0.00108,0.0093,0.9880,0.3945 -1.250,-0.1789,0.00458,0.00099,0.0084,0.9842,0.6337 -1.000,-0.1460,0.00415,0.00095,0.0071,0.9812,0.7466 -0.750,-0.1218,0.00368,0.00094,0.0082,0.9741,0.8636 -0.500,-0.0861,0.00353,0.00091,0.0066,0.9704,0.9043 -0.250,-0.0470,0.00348,0.00092,0.0042,0.9667,0.9316 0.000,0.0000,0.00349,0.00095,0.0000,0.9570,0.9569 0.250,0.0467,0.00349,0.00092,-0.0041,0.9322,0.9671 0.500,0.0862,0.00354,0.00091,-0.0066,0.9038,0.9704 0.750,0.1214,0.00370,0.00093,-0.0081,0.8576,0.9740 1.000,0.1466,0.00413,0.00096,-0.0073,0.7515,0.9811 1.250,0.1784,0.00465,0.00098,-0.0083,0.6135,0.9843 1.500,0.2080,0.00552,0.00108,-0.0093,0.3950,0.9880 1.750,0.2386,0.00626,0.00122,-0.0104,0.2223,0.9918 2.000,0.2684,0.00734,0.00163,-0.0114,0.0162,0.9948 2.250,0.3054,0.00757,0.00191,-0.0135,0.0133,0.9971 2.500,0.3408,0.00810,0.00254,-0.0151,0.0095,0.9993 2.750,0.3673,0.00869,0.00324,-0.0148,0.0094,1.0000 3.000,0.3880,0.00942,0.00406,-0.0131,0.0098,1.0000 3.250,0.4081,0.01061,0.00537,-0.0111,0.0108,1.0000 3.500,0.4292,0.01137,0.00614,-0.0100,0.0086,1.0000 3.750,0.4498,0.01298,0.00798,-0.0083,0.0072,1.0000 4.000,0.4731,0.01332,0.00838,-0.0072,0.0059,1.0000 4.250,0.4943,0.01543,0.01074,-0.0052,0.0055,1.0000 6.000,0.5892,0.04133,0.03880,0.0122,0.0075,1.0000 6.250,0.6014,0.04468,0.04233,0.0137,0.0074,1.0000 6.500,0.6152,0.04771,0.04552,0.0149,0.0072,1.0000 6.750,0.6336,0.05017,0.04809,0.0159,0.0065,1.0000 7.000,0.6428,0.05422,0.05228,0.0164,0.0062,1.0000 7.250,0.6492,0.05859,0.05678,0.0163,0.0060,1.0000 7.500,0.6532,0.06325,0.06154,0.0155,0.0058,1.0000 7.750,0.6541,0.06815,0.06652,0.0137,0.0058,1.0000 8.000,0.6531,0.07322,0.07165,0.0109,0.0057,1.0000 8.250,0.6441,0.07826,0.07670,0.0069,0.0057,1.0000 8.500,0.6386,0.08322,0.08163,0.0023,0.0058,1.0000