Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe244-il-100000 Airfoil,goe244-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,50.1139 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe244-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -6.000,0.1290,0.11042,0.10594,-0.0882,0.7978,0.1150 -5.750,0.0950,0.11181,0.10739,-0.0872,0.7886,0.1171 -5.500,0.0802,0.11071,0.10635,-0.0863,0.7781,0.1180 -5.250,0.1272,0.10518,0.10078,-0.0853,0.7767,0.1210 -5.000,0.1355,0.10337,0.09898,-0.0844,0.7698,0.1247 -4.750,0.1155,0.10353,0.09919,-0.0942,0.7572,0.1312 -4.500,0.1086,0.10180,0.09751,-0.0865,0.7474,0.1319 -4.250,0.1307,0.09868,0.09438,-0.0824,0.7423,0.1348 -3.750,0.1954,0.09058,0.08621,-0.0922,0.7365,0.1491 -3.500,0.1984,0.09059,0.08623,-0.1017,0.7204,0.1602 -3.250,0.2217,0.08607,0.08172,-0.0980,0.7187,0.1627 -3.000,0.2585,0.08245,0.07806,-0.0982,0.7174,0.1698 -2.750,0.5751,0.04770,0.04142,-0.2033,0.7196,0.1051 -2.500,0.6607,0.04215,0.03547,-0.2145,0.7194,0.0997 -2.250,0.7547,0.03765,0.03005,-0.2260,0.7193,0.0958 -2.000,0.7730,0.03737,0.02962,-0.2249,0.7068,0.0959 -1.750,0.8356,0.03475,0.02682,-0.2295,0.7045,0.0977 -1.500,0.8994,0.03233,0.02424,-0.2341,0.7022,0.1036 -1.250,0.9618,0.02987,0.02180,-0.2385,0.6996,0.1115 -1.000,0.9810,0.02970,0.02162,-0.2367,0.6862,0.1171 -0.750,1.0480,0.02737,0.01942,-0.2425,0.6816,0.1492 -0.500,1.0773,0.02719,0.01975,-0.2426,0.6682,0.3276 -0.250,1.1225,0.02662,0.01903,-0.2436,0.6615,0.3831 0.000,1.1369,0.02710,0.01954,-0.2405,0.6467,0.4048 0.250,1.1587,0.02737,0.01977,-0.2385,0.6336,0.4261 0.500,1.1944,0.02715,0.01941,-0.2382,0.6240,0.4502 0.750,1.2149,0.02743,0.01958,-0.2369,0.6090,0.4657 1.000,1.2366,0.02761,0.01970,-0.2353,0.5961,0.4758 1.250,1.2759,0.02729,0.01910,-0.2368,0.5860,0.4917 1.500,1.2948,0.02772,0.01944,-0.2355,0.5726,0.5056 1.750,1.3207,0.02790,0.01952,-0.2350,0.5626,0.5180 2.000,1.3475,0.02809,0.01958,-0.2348,0.5526,0.5321 2.250,1.3747,0.02838,0.01975,-0.2349,0.5439,0.5479 2.500,1.4000,0.02871,0.01999,-0.2346,0.5353,0.5651 2.750,1.4330,0.02888,0.01998,-0.2355,0.5287,0.5847 3.000,1.4491,0.02956,0.02071,-0.2338,0.5207,0.6025 3.250,1.4793,0.02977,0.02079,-0.2341,0.5145,0.6234 3.500,1.5036,0.03027,0.02124,-0.2337,0.5085,0.6433 3.750,1.5211,0.03094,0.02194,-0.2323,0.5020,0.6615 4.000,1.5508,0.03125,0.02213,-0.2327,0.4967,0.6818 4.250,1.5841,0.03161,0.02234,-0.2337,0.4924,0.7030 4.500,1.5938,0.03262,0.02350,-0.2312,0.4873,0.7188 4.750,1.6132,0.03334,0.02424,-0.2302,0.4828,0.7371 5.000,1.6417,0.03379,0.02461,-0.2305,0.4788,0.7578 5.250,1.6795,0.03412,0.02478,-0.2324,0.4754,0.7819 5.500,1.6904,0.03521,0.02602,-0.2302,0.4718,0.8013 5.750,1.6971,0.03638,0.02737,-0.2275,0.4679,0.8231 6.000,1.7101,0.03719,0.02834,-0.2256,0.4642,0.8601 6.250,1.7360,0.03779,0.02893,-0.2258,0.4607,1.0000 6.500,1.7781,0.03836,0.02931,-0.2287,0.4576,1.0000 6.750,1.7995,0.03972,0.03066,-0.2285,0.4548,1.0000 7.000,1.7898,0.04192,0.03309,-0.2238,0.4517,1.0000 7.250,1.7785,0.04423,0.03557,-0.2190,0.4487,1.0000 7.500,1.7726,0.04654,0.03800,-0.2152,0.4457,1.0000 7.750,1.7857,0.04803,0.03950,-0.2139,0.4427,1.0000 8.000,1.8424,0.04750,0.03873,-0.2180,0.4393,1.0000 8.250,1.8452,0.04943,0.04072,-0.2152,0.4356,1.0000 8.500,1.1220,0.14479,0.13842,-0.1933,0.4182,0.8152