Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe511-il-50000-n5 Airfoil,goe511-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,25.2317 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe511-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.0598,0.12073,0.11443,-0.0669,0.9211,0.1355 -8.750,-0.0689,0.11931,0.11305,-0.0708,0.9103,0.1381 -8.500,-0.0696,0.11658,0.11038,-0.0719,0.8983,0.1390 -8.250,-0.0295,0.11121,0.10497,-0.0726,0.8933,0.1437 -8.000,-0.0269,0.10886,0.10266,-0.0729,0.8808,0.1481 -7.750,-0.0446,0.10773,0.10158,-0.0745,0.8664,0.1520 -7.500,-0.0683,0.10663,0.10052,-0.0747,0.8509,0.1527 -7.250,-0.0432,0.10174,0.09564,-0.0754,0.8427,0.1542 -6.750,-0.0349,0.09607,0.09000,-0.0737,0.8173,0.1565 -6.500,-0.0601,0.08847,0.08215,-0.0778,0.8030,0.0968 -6.000,-0.0649,0.08035,0.07382,-0.0784,0.7779,0.0872 -5.750,-0.0532,0.07699,0.07036,-0.0785,0.7689,0.0867 -5.500,-0.0444,0.07375,0.06701,-0.0782,0.7586,0.0863 -5.250,-0.0356,0.07067,0.06381,-0.0776,0.7483,0.0858 -5.000,-0.0206,0.06716,0.06014,-0.0777,0.7399,0.0848 -4.750,-0.0101,0.06400,0.05681,-0.0770,0.7299,0.0837 -4.500,0.0053,0.06035,0.05291,-0.0769,0.7214,0.0825 -4.250,0.0214,0.05658,0.04882,-0.0767,0.7135,0.0814 -4.000,0.0332,0.05352,0.04546,-0.0753,0.7031,0.0812 -3.750,0.0613,0.04994,0.04148,-0.0760,0.6978,0.0825 -3.500,0.0667,0.04820,0.03946,-0.0729,0.6849,0.0832 -3.250,0.0946,0.04485,0.03559,-0.0730,0.6789,0.0840 -3.000,0.1046,0.04324,0.03361,-0.0702,0.6673,0.0842 -2.750,0.1337,0.04072,0.03055,-0.0700,0.6604,0.0849 -2.500,0.1524,0.03929,0.02869,-0.0683,0.6505,0.0858 -2.250,0.1806,0.03772,0.02664,-0.0678,0.6423,0.0880 -2.000,0.2100,0.03676,0.02553,-0.0678,0.6342,0.0909 -1.750,0.2327,0.03609,0.02463,-0.0668,0.6245,0.0936 -1.500,0.2823,0.03447,0.02252,-0.0697,0.6186,0.0970 -1.250,0.2989,0.03444,0.02234,-0.0679,0.6074,0.0993 -1.000,0.3591,0.03336,0.02100,-0.0731,0.6008,0.1080 -0.750,0.3863,0.03336,0.02092,-0.0732,0.5908,0.1144 -0.500,0.4349,0.03265,0.02007,-0.0765,0.5834,0.1264 -0.250,0.4596,0.03267,0.02020,-0.0759,0.5752,0.1419 0.000,0.4865,0.03265,0.02032,-0.0756,0.5672,0.1705 0.250,0.5249,0.03247,0.02004,-0.0769,0.5611,0.2355 0.500,0.5291,0.03317,0.02074,-0.0730,0.5521,0.2650 0.750,0.5584,0.03316,0.02065,-0.0731,0.5457,0.3134 1.000,0.5808,0.03330,0.02078,-0.0723,0.5391,0.3562 1.250,0.5922,0.03370,0.02125,-0.0698,0.5317,0.3840 1.500,0.6257,0.03343,0.02092,-0.0708,0.5259,0.4152 1.750,0.6511,0.03348,0.02093,-0.0705,0.5202,0.4370 2.000,0.6527,0.03422,0.02178,-0.0665,0.5129,0.4522 2.500,0.8564,0.03459,0.02275,-0.0954,0.4977,1.0000 2.750,0.8576,0.03549,0.02358,-0.0912,0.4920,1.0000 3.000,0.8779,0.03603,0.02393,-0.0900,0.4872,1.0000 3.250,0.9149,0.03626,0.02387,-0.0915,0.4833,1.0000 3.500,0.8914,0.03778,0.02550,-0.0836,0.4776,1.0000 3.750,0.8839,0.03908,0.02680,-0.0784,0.4720,1.0000 4.000,0.9013,0.03971,0.02729,-0.0769,0.4676,1.0000 4.250,0.9339,0.03991,0.02728,-0.0776,0.4643,1.0000 4.500,0.9041,0.04222,0.02972,-0.0698,0.4588,1.0000 4.750,0.8711,0.04518,0.03281,-0.0625,0.4526,1.0000 5.000,0.8784,0.04647,0.03403,-0.0602,0.4487,1.0000 5.250,0.9051,0.04677,0.03420,-0.0600,0.4460,1.0000 5.750,0.7964,0.05816,0.04595,-0.0465,0.4294,1.0000 6.000,0.8204,0.05844,0.04611,-0.0458,0.4272,1.0000 6.250,0.8504,0.05828,0.04581,-0.0456,0.4256,1.0000 6.750,0.7519,0.07384,0.06169,-0.0400,0.4080,1.0000 7.750,0.6842,0.09393,0.08194,-0.0369,0.3849,1.0000 8.000,0.6766,0.09780,0.08583,-0.0364,0.3797,1.0000 8.250,0.6850,0.09996,0.08795,-0.0359,0.3766,1.0000 8.500,0.7016,0.10121,0.08914,-0.0354,0.3742,1.0000 8.750,0.7247,0.10168,0.08955,-0.0347,0.3722,1.0000 9.000,0.6879,0.10876,0.09675,-0.0347,0.3636,1.0000 9.250,0.6965,0.11080,0.09877,-0.0342,0.3596,1.0000 9.500,0.7158,0.11162,0.09953,-0.0336,0.3565,1.0000 9.750,0.7414,0.11176,0.09961,-0.0329,0.3544,1.0000 10.000,0.7089,0.11823,0.10618,-0.0332,0.3448,1.0000 10.250,0.7237,0.11945,0.10737,-0.0327,0.3406,1.0000