Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe484-il-100000 Airfoil,goe484-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,67.3024 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-goe484-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.750,-0.3637,0.10331,0.09841,-0.0261,1.0000,0.0758 -7.500,-0.3830,0.10369,0.09890,-0.0239,1.0000,0.0765 -7.250,-0.3969,0.10385,0.09916,-0.0252,1.0000,0.0771 -7.000,-0.4016,0.10344,0.09880,-0.0304,1.0000,0.0774 -6.750,-0.3960,0.09657,0.09197,-0.0217,1.0000,0.0789 -6.500,-0.3924,0.09352,0.08895,-0.0188,1.0000,0.0806 -6.250,-0.3915,0.09119,0.08665,-0.0175,1.0000,0.0825 -6.000,-0.3907,0.08893,0.08441,-0.0172,1.0000,0.0848 -5.750,-0.3881,0.08666,0.08217,-0.0186,1.0000,0.0878 -5.500,-0.3612,0.08504,0.08043,-0.0374,1.0000,0.0916 -5.250,-0.3658,0.08066,0.07615,-0.0303,1.0000,0.0926 -5.000,-0.3648,0.07773,0.07327,-0.0257,1.0000,0.0944 -4.750,-0.3573,0.07522,0.07077,-0.0247,1.0000,0.0978 -4.250,-0.3134,0.06833,0.06375,-0.0366,1.0000,0.1079 -4.000,-0.3054,0.06574,0.06119,-0.0348,1.0000,0.1104 -3.750,-0.2759,0.06298,0.05829,-0.0408,1.0000,0.1188 -3.500,-0.2498,0.05910,0.05432,-0.0457,1.0000,0.1229 -3.250,-0.2021,0.05722,0.05203,-0.0557,1.0000,0.1358 -3.000,-0.1969,0.05342,0.04843,-0.0528,1.0000,0.1375 -2.750,-0.1797,0.05119,0.04625,-0.0523,0.9987,0.1433 -2.500,-0.1084,0.04832,0.04286,-0.0661,0.9928,0.1658 -2.250,-0.0801,0.04488,0.03957,-0.0675,0.9869,0.1702 -2.000,-0.0345,0.04232,0.03685,-0.0734,0.9810,0.1857 -1.750,0.0139,0.04012,0.03439,-0.0798,0.9743,0.2113 -1.500,0.0514,0.03797,0.03224,-0.0829,0.9677,0.2301 -1.250,0.1350,0.03233,0.02493,-0.0932,0.9644,0.1214 -1.000,0.1810,0.02941,0.02157,-0.0967,0.9597,0.1028 -0.750,0.2219,0.02761,0.01935,-0.0992,0.9531,0.0968 -0.500,0.2644,0.02622,0.01746,-0.1017,0.9464,0.0937 -0.250,0.3032,0.02537,0.01645,-0.1038,0.9387,0.0946 0.000,0.3436,0.02487,0.01590,-0.1062,0.9311,0.1008 0.250,0.3785,0.02441,0.01533,-0.1075,0.9220,0.1054 0.500,0.4205,0.02377,0.01483,-0.1101,0.9158,0.1137 0.750,0.4524,0.02342,0.01457,-0.1108,0.9055,0.1289 1.000,0.5009,0.02157,0.01424,-0.1150,0.9019,0.5707 1.250,0.5352,0.02106,0.01412,-0.1160,0.8922,1.0000 1.500,0.5788,0.02114,0.01403,-0.1188,0.8861,1.0000 1.750,0.6076,0.02140,0.01420,-0.1191,0.8749,1.0000 2.000,0.6539,0.02135,0.01408,-0.1223,0.8705,1.0000 2.250,0.6791,0.02166,0.01438,-0.1219,0.8588,1.0000 2.500,0.7113,0.02178,0.01450,-0.1225,0.8489,1.0000 2.750,0.7639,0.02104,0.01380,-0.1260,0.8425,1.0000 3.000,0.8020,0.02052,0.01334,-0.1268,0.8302,1.0000 3.250,0.8504,0.01908,0.01197,-0.1281,0.8158,1.0000 3.500,0.9012,0.01720,0.01013,-0.1291,0.7968,1.0000 3.750,0.9296,0.01666,0.00968,-0.1277,0.7755,1.0000 4.000,0.9624,0.01590,0.00895,-0.1267,0.7508,1.0000 4.250,0.9848,0.01549,0.00857,-0.1241,0.7147,1.0000 4.500,1.0108,0.01511,0.00810,-0.1219,0.6653,1.0000 4.750,1.0304,0.01531,0.00785,-0.1184,0.5771,1.0000 5.000,1.0294,0.01682,0.00808,-0.1120,0.3507,1.0000 5.250,1.0258,0.01984,0.00950,-0.1071,0.1391,1.0000 5.500,1.0388,0.02129,0.01068,-0.1045,0.1165,1.0000 5.750,1.0547,0.02237,0.01179,-0.1022,0.1075,1.0000 6.000,1.0679,0.02372,0.01311,-0.0996,0.1013,1.0000 6.250,1.0854,0.02482,0.01426,-0.0977,0.0952,1.0000 6.500,1.1039,0.02630,0.01564,-0.0960,0.0908,1.0000 6.750,1.1309,0.02822,0.01745,-0.0957,0.0876,1.0000 7.000,1.1583,0.02963,0.01897,-0.0953,0.0835,1.0000 7.250,1.1881,0.03144,0.02084,-0.0954,0.0797,1.0000 7.500,1.2215,0.03389,0.02330,-0.0961,0.0773,1.0000 7.750,1.2519,0.03705,0.02660,-0.0964,0.0743,1.0000 8.000,1.2755,0.03928,0.02922,-0.0952,0.0731,1.0000 8.250,1.2984,0.04224,0.03259,-0.0939,0.0730,1.0000 8.500,1.3166,0.04510,0.03589,-0.0920,0.0723,1.0000 8.750,1.3313,0.04816,0.03940,-0.0897,0.0716,1.0000 9.000,1.3463,0.05262,0.04423,-0.0878,0.0734,1.0000 9.250,1.3510,0.05688,0.04944,-0.0831,0.0825,1.0000 11.750,1.0876,0.13785,0.13328,-0.0871,0.1854,1.0000 12.000,1.0395,0.14522,0.14051,-0.0964,0.1755,1.0000