Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe587-il-1000000 Airfoil,goe587-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,77.9368 Max Cl/Cd alpha,2.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe587-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.4621,0.08879,0.08721,-0.0132,1.0000,0.0064 -7.750,-0.4649,0.08567,0.08412,-0.0146,1.0000,0.0064 -7.500,-0.4632,0.08217,0.08062,-0.0164,1.0000,0.0064 -7.250,-0.4582,0.07859,0.07704,-0.0184,1.0000,0.0064 -7.000,-0.4608,0.07280,0.07125,-0.0208,1.0000,0.0066 -6.750,-0.4567,0.06868,0.06712,-0.0222,1.0000,0.0068 -6.500,-0.4484,0.06548,0.06389,-0.0230,1.0000,0.0070 -6.250,-0.4389,0.06232,0.06070,-0.0236,1.0000,0.0071 -6.000,-0.4283,0.05925,0.05759,-0.0241,1.0000,0.0073 -5.750,-0.4167,0.05595,0.05424,-0.0244,1.0000,0.0075 -5.500,-0.4044,0.05289,0.05112,-0.0244,1.0000,0.0077 -4.000,-0.2234,0.02390,0.02087,-0.0377,0.9726,0.0095 -3.750,-0.1953,0.01762,0.01404,-0.0371,0.9623,0.0096 -3.500,-0.1609,0.01325,0.00907,-0.0381,0.9527,0.0098 -3.250,-0.1214,0.01138,0.00687,-0.0405,0.9394,0.0104 -3.000,-0.0840,0.00951,0.00464,-0.0424,0.9189,0.0107 -2.750,-0.0559,0.00838,0.00320,-0.0422,0.8940,0.0117 -2.500,-0.0313,0.00777,0.00243,-0.0414,0.8706,0.0144 -2.250,-0.0064,0.00758,0.00212,-0.0406,0.8474,0.0165 -2.000,0.0193,0.00762,0.00209,-0.0401,0.8231,0.0185 -1.750,0.0428,0.00721,0.00155,-0.0391,0.7990,0.0261 -1.500,0.0683,0.00726,0.00149,-0.0385,0.7757,0.0296 -1.250,0.0928,0.00710,0.00124,-0.0378,0.7538,0.0386 -1.000,0.1186,0.00712,0.00118,-0.0374,0.7339,0.0416 -0.750,0.1439,0.00700,0.00097,-0.0368,0.7157,0.0472 -0.500,0.1695,0.00695,0.00086,-0.0363,0.6990,0.0550 -0.250,0.1946,0.00679,0.00079,-0.0358,0.6806,0.1032 0.000,0.2186,0.00663,0.00075,-0.0351,0.6513,0.1855 0.250,0.2358,0.00568,0.00072,-0.0335,0.6246,0.5620 0.500,0.2453,0.00479,0.00079,-0.0293,0.6030,0.9019 0.750,0.2686,0.00487,0.00084,-0.0281,0.5829,0.9295 1.000,0.2925,0.00499,0.00090,-0.0270,0.5628,0.9474 1.250,0.3181,0.00511,0.00096,-0.0264,0.5443,0.9605 1.500,0.3487,0.00528,0.00105,-0.0268,0.5250,0.9724 1.750,0.4000,0.00560,0.00126,-0.0319,0.5021,0.9830 2.000,0.4363,0.00576,0.00131,-0.0340,0.4763,0.9843 2.250,0.4684,0.00601,0.00136,-0.0352,0.4219,0.9856 2.500,0.4953,0.00677,0.00154,-0.0356,0.2831,0.9874 2.750,0.5168,0.00816,0.00202,-0.0352,0.0506,0.9896 3.000,0.5501,0.00837,0.00219,-0.0365,0.0401,0.9920 3.250,0.5806,0.00854,0.00241,-0.0373,0.0379,0.9940 3.500,0.6101,0.00876,0.00265,-0.0378,0.0334,0.9949 3.750,0.6388,0.00920,0.00318,-0.0382,0.0275,0.9959 4.000,0.6687,0.00932,0.00330,-0.0389,0.0265,0.9968 4.250,0.6982,0.00950,0.00349,-0.0395,0.0237,0.9979 4.500,0.7254,0.01014,0.00421,-0.0397,0.0170,0.9991 4.750,0.7557,0.01017,0.00422,-0.0405,0.0155,0.9999 5.000,0.7771,0.01044,0.00452,-0.0393,0.0134,1.0000 5.250,0.7962,0.01075,0.00484,-0.0377,0.0118,1.0000 5.500,0.8032,0.01215,0.00643,-0.0335,0.0098,1.0000 5.750,0.8237,0.01223,0.00652,-0.0322,0.0091,1.0000 6.000,0.8387,0.01287,0.00723,-0.0297,0.0086,1.0000 6.250,0.8550,0.01353,0.00797,-0.0275,0.0079,1.0000 6.500,0.8726,0.01422,0.00873,-0.0256,0.0074,1.0000 6.750,0.8915,0.01488,0.00945,-0.0240,0.0069,1.0000 7.000,0.9107,0.01557,0.01020,-0.0226,0.0063,1.0000 7.250,0.9183,0.02014,0.01516,-0.0188,0.0055,1.0000 15.250,0.8228,0.18271,0.18101,-0.0489,0.0054,1.0000 15.500,0.8279,0.18732,0.18561,-0.0510,0.0054,1.0000