Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe05k-il-1000000 Airfoil,goe05k-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,95.1429 Max Cl/Cd alpha,0.75 Url,http://airfoiltools.com/polar/csv?polar=xf-goe05k-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.4275,0.08340,0.08186,-0.0143,1.0000,0.0026 -8.250,-0.4278,0.07976,0.07823,-0.0148,1.0000,0.0026 -8.000,-0.4287,0.07622,0.07471,-0.0152,1.0000,0.0027 -7.750,-0.4302,0.07270,0.07120,-0.0156,1.0000,0.0027 -7.500,-0.4328,0.06933,0.06785,-0.0158,1.0000,0.0027 -7.250,-0.4377,0.06623,0.06478,-0.0157,1.0000,0.0027 -7.000,-0.4469,0.06361,0.06218,-0.0147,1.0000,0.0028 -6.750,-0.4522,0.06047,0.05906,-0.0154,1.0000,0.0028 -1.750,-0.0267,0.00881,0.00377,-0.0430,0.9803,0.0052 -1.500,0.0056,0.00815,0.00300,-0.0438,0.9794,0.0067 -1.250,0.0324,0.00728,0.00202,-0.0434,0.9766,0.0068 -1.000,0.0611,0.00678,0.00144,-0.0435,0.9738,0.0158 -0.750,0.1114,0.00418,0.00168,-0.0499,0.9816,1.0000 -0.500,0.1471,0.00415,0.00157,-0.0519,0.9802,1.0000 -0.250,0.1850,0.00410,0.00146,-0.0543,0.9790,1.0000 0.000,0.2189,0.00395,0.00129,-0.0557,0.9731,1.0000 0.250,0.2612,0.00379,0.00113,-0.0590,0.9697,1.0000 0.500,0.2956,0.00364,0.00099,-0.0605,0.9609,1.0000 0.750,0.3330,0.00350,0.00088,-0.0626,0.9482,1.0000 1.250,0.3884,0.00421,0.00067,-0.0619,0.6811,1.0000 1.500,0.3847,0.00664,0.00109,-0.0560,0.1342,1.0000 1.750,0.4028,0.00761,0.00169,-0.0538,0.0073,1.0000 2.000,0.4247,0.00818,0.00235,-0.0523,0.0047,1.0000 2.250,0.4433,0.00926,0.00351,-0.0501,0.0051,1.0000 4.500,0.6158,0.01130,0.00783,-0.0295,0.0032,1.0000 4.750,0.6354,0.01398,0.01078,-0.0270,0.0029,1.0000 5.000,0.6521,0.01716,0.01421,-0.0248,0.0026,1.0000 5.250,0.6673,0.02066,0.01793,-0.0229,0.0024,1.0000 5.500,0.6809,0.02439,0.02186,-0.0212,0.0023,1.0000 5.750,0.6910,0.02848,0.02611,-0.0199,0.0021,1.0000 6.000,0.6960,0.03376,0.03156,-0.0186,0.0021,1.0000 6.250,0.7054,0.03849,0.03646,-0.0172,0.0021,1.0000 6.500,0.7130,0.04333,0.04143,-0.0162,0.0021,1.0000 6.750,0.7181,0.04838,0.04661,-0.0154,0.0020,1.0000 7.000,0.7204,0.05337,0.05171,-0.0150,0.0020,1.0000 7.250,0.7195,0.05829,0.05671,-0.0148,0.0020,1.0000 7.500,0.7150,0.06322,0.06171,-0.0151,0.0020,1.0000 7.750,0.7036,0.06724,0.06577,-0.0147,0.0020,1.0000 8.000,0.6882,0.07145,0.07001,-0.0158,0.0020,1.0000 8.250,0.6742,0.07667,0.07523,-0.0201,0.0020,1.0000 8.500,0.6668,0.08189,0.08044,-0.0230,0.0021,1.0000