Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe587-il-100000 Airfoil,goe587-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,50.1329 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-goe587-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.4588,0.09610,0.09123,-0.0129,1.0000,0.0526 -7.750,-0.4615,0.09366,0.08887,-0.0153,1.0000,0.0536 -7.500,-0.4624,0.09153,0.08679,-0.0195,1.0000,0.0545 -7.250,-0.4578,0.08947,0.08469,-0.0241,1.0000,0.0550 -7.000,-0.4502,0.08720,0.08234,-0.0274,1.0000,0.0553 -6.750,-0.4468,0.07951,0.07485,-0.0215,1.0000,0.0581 -6.500,-0.4395,0.07619,0.07155,-0.0213,1.0000,0.0615 -6.250,-0.4301,0.07319,0.06846,-0.0235,1.0000,0.0661 -6.000,-0.4125,0.07276,0.06772,-0.0297,1.0000,0.0687 -5.750,-0.4095,0.06610,0.06124,-0.0269,1.0000,0.0707 -5.500,-0.4005,0.06264,0.05781,-0.0257,1.0000,0.0738 -5.250,-0.3849,0.05986,0.05490,-0.0268,1.0000,0.0800 -5.000,-0.3699,0.05653,0.05138,-0.0280,1.0000,0.0835 -4.750,-0.3603,0.05299,0.04791,-0.0263,1.0000,0.0875 -4.500,-0.3400,0.05093,0.04547,-0.0273,1.0000,0.0966 -4.250,-0.3305,0.04712,0.04180,-0.0255,1.0000,0.1005 -4.000,-0.3133,0.04469,0.03911,-0.0251,1.0000,0.1111 -3.500,-0.2859,0.03941,0.03372,-0.0224,1.0000,0.1296 -3.250,-0.2704,0.03779,0.03177,-0.0212,1.0000,0.1512 -3.000,-0.2601,0.03523,0.02932,-0.0192,1.0000,0.1727 -2.250,-0.2269,0.02919,0.02322,-0.0132,1.0000,0.2774 -2.000,-0.1620,0.02483,0.01678,-0.0131,1.0000,0.0805 -1.750,-0.1411,0.02274,0.01443,-0.0119,1.0000,0.0760 -1.500,-0.1202,0.02180,0.01304,-0.0103,1.0000,0.0813 -1.250,-0.0868,0.01994,0.01091,-0.0114,0.9964,0.0848 -1.000,-0.0393,0.01859,0.00932,-0.0151,0.9871,0.0967 -0.750,0.0064,0.01731,0.00806,-0.0187,0.9772,0.1159 -0.500,0.0518,0.01631,0.00720,-0.0224,0.9664,0.1467 -0.250,0.1325,0.01316,0.00633,-0.0315,0.9738,1.0000 0.000,0.1873,0.01322,0.00606,-0.0373,0.9602,1.0000 0.250,0.2426,0.01319,0.00584,-0.0431,0.9470,1.0000 0.500,0.2990,0.01305,0.00560,-0.0489,0.9338,1.0000 0.750,0.3523,0.01286,0.00536,-0.0540,0.9191,1.0000 1.000,0.4025,0.01266,0.00512,-0.0583,0.9026,1.0000 1.250,0.4396,0.01262,0.00506,-0.0599,0.8808,1.0000 1.500,0.4734,0.01263,0.00504,-0.0607,0.8604,1.0000 1.750,0.4991,0.01277,0.00521,-0.0599,0.8384,1.0000 2.000,0.5241,0.01291,0.00534,-0.0589,0.8188,1.0000 2.250,0.5452,0.01295,0.00532,-0.0566,0.7929,1.0000 2.500,0.5645,0.01300,0.00530,-0.0539,0.7640,1.0000 2.750,0.5857,0.01317,0.00548,-0.0521,0.7423,1.0000 3.000,0.6068,0.01334,0.00566,-0.0503,0.7203,1.0000 3.250,0.6273,0.01346,0.00585,-0.0481,0.6955,1.0000 3.500,0.6479,0.01360,0.00605,-0.0461,0.6717,1.0000 3.750,0.6642,0.01353,0.00594,-0.0428,0.6277,1.0000 4.000,0.6788,0.01354,0.00583,-0.0390,0.5657,1.0000 4.250,0.6896,0.01393,0.00583,-0.0346,0.4468,1.0000 4.500,0.6860,0.01690,0.00673,-0.0296,0.1109,1.0000 4.750,0.7014,0.01821,0.00799,-0.0272,0.0856,1.0000 5.000,0.7161,0.01949,0.00941,-0.0247,0.0766,1.0000 5.250,0.7322,0.02064,0.01063,-0.0223,0.0688,1.0000 5.500,0.7480,0.02226,0.01219,-0.0200,0.0622,1.0000 5.750,0.7705,0.02403,0.01396,-0.0185,0.0596,1.0000 6.000,0.7973,0.02619,0.01619,-0.0174,0.0588,1.0000 6.250,0.8234,0.02851,0.01862,-0.0165,0.0563,1.0000 6.500,0.8477,0.03162,0.02184,-0.0157,0.0537,1.0000 6.750,0.8723,0.03405,0.02505,-0.0133,0.0596,1.0000 7.000,0.8969,0.03737,0.02895,-0.0110,0.0696,1.0000 10.250,0.8432,0.10453,0.09989,-0.0113,0.1559,1.0000 10.500,0.8087,0.11116,0.10631,-0.0193,0.1530,1.0000 10.750,0.6926,0.11342,0.10888,-0.0164,0.1684,1.0000