Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe587-il-100000-n5 Airfoil,goe587-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,50.6943 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe587-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.4508,0.10518,0.10028,-0.0160,1.0000,0.0302 -8.250,-0.4496,0.10223,0.09739,-0.0179,1.0000,0.0303 -8.000,-0.4488,0.09937,0.09459,-0.0196,1.0000,0.0303 -7.750,-0.4460,0.09626,0.09152,-0.0221,1.0000,0.0304 -7.500,-0.4405,0.09301,0.08829,-0.0246,1.0000,0.0304 -7.250,-0.4335,0.08961,0.08489,-0.0267,1.0000,0.0305 -7.000,-0.4307,0.08378,0.07916,-0.0211,1.0000,0.0323 -6.750,-0.4248,0.08054,0.07594,-0.0218,1.0000,0.0336 -6.500,-0.4180,0.07725,0.07266,-0.0233,1.0000,0.0347 -6.250,-0.4097,0.07395,0.06937,-0.0249,1.0000,0.0359 -6.000,-0.3998,0.07063,0.06602,-0.0264,1.0000,0.0368 -5.750,-0.3866,0.06739,0.06271,-0.0285,1.0000,0.0383 -5.250,-0.3502,0.06165,0.05658,-0.0322,1.0000,0.0398 -5.000,-0.3359,0.05824,0.05304,-0.0321,1.0000,0.0398 -4.500,-0.3208,0.04904,0.04390,-0.0294,1.0000,0.0261 -4.000,-0.2791,0.04122,0.03547,-0.0281,1.0000,0.0201 -3.750,-0.2654,0.03793,0.03200,-0.0269,1.0000,0.0197 -3.500,-0.2458,0.03462,0.02842,-0.0262,0.9987,0.0195 -3.000,-0.1750,0.02771,0.02066,-0.0305,0.9828,0.0228 -2.750,-0.1393,0.02453,0.01689,-0.0317,0.9745,0.0234 -2.500,-0.1030,0.02168,0.01345,-0.0328,0.9666,0.0250 -2.250,-0.0671,0.01958,0.01072,-0.0336,0.9574,0.0300 -2.000,-0.0329,0.01786,0.00880,-0.0346,0.9476,0.0349 -1.750,0.0031,0.01662,0.00739,-0.0361,0.9383,0.0476 -1.500,0.0391,0.01556,0.00619,-0.0376,0.9285,0.0666 -1.250,0.0732,0.01485,0.00544,-0.0388,0.9165,0.0844 -1.000,0.1078,0.01427,0.00476,-0.0400,0.9041,0.1011 -0.750,0.1422,0.01373,0.00417,-0.0412,0.8909,0.1337 -0.500,0.2393,0.01135,0.00398,-0.0550,0.8968,1.0000 -0.250,0.2750,0.01130,0.00367,-0.0565,0.8781,1.0000 0.000,0.3081,0.01129,0.00346,-0.0575,0.8584,1.0000 0.250,0.3366,0.01132,0.00333,-0.0575,0.8372,1.0000 0.500,0.3643,0.01137,0.00324,-0.0574,0.8172,1.0000 0.750,0.3904,0.01145,0.00320,-0.0569,0.7967,1.0000 1.000,0.4164,0.01153,0.00318,-0.0564,0.7778,1.0000 1.250,0.4417,0.01164,0.00320,-0.0558,0.7593,1.0000 1.500,0.4662,0.01177,0.00328,-0.0550,0.7410,1.0000 1.750,0.4905,0.01191,0.00337,-0.0542,0.7238,1.0000 2.000,0.5144,0.01207,0.00349,-0.0533,0.7076,1.0000 2.250,0.5381,0.01223,0.00366,-0.0524,0.6922,1.0000 2.500,0.5610,0.01240,0.00387,-0.0513,0.6738,1.0000 2.750,0.5826,0.01257,0.00401,-0.0499,0.6491,1.0000 3.000,0.6035,0.01273,0.00413,-0.0482,0.6196,1.0000 3.250,0.6247,0.01292,0.00430,-0.0467,0.5923,1.0000 3.500,0.6469,0.01312,0.00462,-0.0455,0.5715,1.0000 3.750,0.6679,0.01337,0.00488,-0.0439,0.5429,1.0000 4.000,0.6892,0.01363,0.00522,-0.0424,0.5159,1.0000 4.250,0.7082,0.01397,0.00555,-0.0405,0.4664,1.0000 4.500,0.7158,0.01529,0.00584,-0.0368,0.2579,1.0000 4.750,0.7217,0.01777,0.00722,-0.0338,0.0634,1.0000 5.000,0.7373,0.01908,0.00858,-0.0317,0.0444,1.0000 5.250,0.7516,0.02047,0.01014,-0.0294,0.0348,1.0000 5.500,0.7663,0.02175,0.01159,-0.0271,0.0286,1.0000 5.750,0.7805,0.02329,0.01321,-0.0248,0.0248,1.0000 6.000,0.7989,0.02495,0.01498,-0.0228,0.0223,1.0000 6.250,0.8190,0.02652,0.01663,-0.0215,0.0187,1.0000 6.500,0.8402,0.02936,0.01955,-0.0205,0.0169,1.0000 6.750,0.8640,0.03179,0.02230,-0.0192,0.0164,1.0000 7.000,0.8856,0.03453,0.02542,-0.0178,0.0160,1.0000 7.250,0.9044,0.03739,0.02874,-0.0159,0.0155,1.0000 7.500,0.9205,0.04017,0.03199,-0.0139,0.0147,1.0000 7.750,0.9334,0.04317,0.03546,-0.0117,0.0137,1.0000 8.000,0.9430,0.04652,0.03925,-0.0095,0.0136,1.0000 8.250,0.9491,0.05012,0.04326,-0.0073,0.0137,1.0000 8.500,0.9518,0.05381,0.04733,-0.0050,0.0138,1.0000 8.750,0.9511,0.05752,0.05137,-0.0029,0.0141,1.0000 9.000,0.9468,0.06120,0.05532,-0.0009,0.0143,1.0000 9.250,0.9388,0.06481,0.05917,0.0010,0.0144,1.0000 9.500,0.9264,0.06802,0.06256,0.0031,0.0146,1.0000 9.750,0.9105,0.07166,0.06635,0.0041,0.0147,1.0000 10.000,0.8948,0.07567,0.07050,0.0036,0.0148,1.0000 10.250,0.8787,0.08040,0.07534,0.0016,0.0149,1.0000 10.500,0.8639,0.08574,0.08078,-0.0017,0.0150,1.0000