Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe372-il-500000 Airfoil,goe372-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,108.576 Max Cl/Cd alpha,2.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe372-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.3537,0.10033,0.09810,-0.0293,1.0000,0.0183 -8.500,-0.3518,0.09746,0.09526,-0.0300,1.0000,0.0184 -8.250,-0.3510,0.09460,0.09243,-0.0303,1.0000,0.0184 -8.000,-0.2919,0.07606,0.07410,-0.0325,1.0000,0.0191 -7.750,-0.2902,0.07383,0.07190,-0.0305,1.0000,0.0197 -7.500,-0.2912,0.07264,0.07075,-0.0279,1.0000,0.0205 -7.250,-0.2823,0.06909,0.06721,-0.0302,0.9979,0.0213 -7.000,-0.2682,0.06449,0.06260,-0.0349,0.9939,0.0222 -6.750,-0.2539,0.05975,0.05787,-0.0403,0.9875,0.0232 -5.750,-0.2074,0.04545,0.04314,-0.0791,0.9741,0.0179 -5.500,-0.1639,0.01886,0.01500,-0.0991,0.9668,0.0183 -5.250,-0.1341,0.01588,0.01154,-0.1009,0.9609,0.0212 -5.000,-0.0984,0.01547,0.01103,-0.1026,0.9572,0.0241 -4.750,-0.0675,0.01467,0.00998,-0.1032,0.9498,0.0267 -4.500,-0.0367,0.01273,0.00768,-0.1043,0.9434,0.0311 -4.250,-0.0068,0.01265,0.00754,-0.1046,0.9346,0.0350 -4.000,0.0245,0.01209,0.00678,-0.1052,0.9273,0.0375 -3.750,0.0521,0.01108,0.00552,-0.1052,0.9171,0.0398 -3.500,0.0795,0.01039,0.00472,-0.1050,0.9068,0.0426 -3.250,0.1075,0.01006,0.00429,-0.1049,0.8970,0.0453 -3.000,0.1352,0.00973,0.00382,-0.1047,0.8874,0.0481 -2.750,0.1619,0.00941,0.00340,-0.1043,0.8767,0.0497 -2.500,0.1883,0.00899,0.00287,-0.1039,0.8668,0.0514 -2.250,0.2148,0.00863,0.00247,-0.1035,0.8577,0.0550 -2.000,0.2416,0.00848,0.00226,-0.1031,0.8482,0.0595 -1.750,0.2681,0.00828,0.00204,-0.1027,0.8388,0.0692 -1.500,0.2950,0.00818,0.00191,-0.1024,0.8302,0.0840 -1.250,0.3216,0.00809,0.00179,-0.1020,0.8212,0.0941 -1.000,0.3484,0.00804,0.00172,-0.1017,0.8125,0.1022 -0.750,0.3751,0.00796,0.00161,-0.1013,0.8041,0.1103 -0.500,0.4017,0.00791,0.00155,-0.1010,0.7947,0.1186 -0.250,0.4283,0.00784,0.00149,-0.1006,0.7856,0.1309 0.000,0.4546,0.00777,0.00145,-0.1002,0.7759,0.1496 0.250,0.4805,0.00763,0.00143,-0.0998,0.7646,0.1920 0.500,0.5055,0.00730,0.00147,-0.0993,0.7530,0.3285 0.750,0.5508,0.00581,0.00153,-0.1035,0.7423,1.0000 1.000,0.5767,0.00589,0.00153,-0.1030,0.7308,1.0000 1.250,0.6024,0.00597,0.00154,-0.1024,0.7175,1.0000 1.500,0.6281,0.00606,0.00156,-0.1018,0.7033,1.0000 1.750,0.6536,0.00615,0.00159,-0.1012,0.6875,1.0000 2.000,0.6786,0.00627,0.00162,-0.1005,0.6673,1.0000 2.250,0.7014,0.00646,0.00163,-0.0993,0.6251,1.0000 2.500,0.7236,0.00675,0.00170,-0.0980,0.5777,1.0000 2.750,0.7463,0.00707,0.00182,-0.0969,0.5414,1.0000 3.000,0.7690,0.00743,0.00198,-0.0959,0.5018,1.0000 3.250,0.7898,0.00794,0.00216,-0.0945,0.4309,1.0000 3.500,0.8006,0.00956,0.00275,-0.0918,0.2238,1.0000 3.750,0.8121,0.01132,0.00362,-0.0893,0.0313,1.0000 4.000,0.8364,0.01168,0.00397,-0.0885,0.0218,1.0000 4.250,0.8605,0.01204,0.00441,-0.0877,0.0196,1.0000 4.500,0.8839,0.01249,0.00495,-0.0868,0.0177,1.0000 4.750,0.9062,0.01307,0.00561,-0.0856,0.0163,1.0000 5.000,0.9269,0.01384,0.00650,-0.0841,0.0154,1.0000 5.250,0.9461,0.01474,0.00749,-0.0824,0.0151,1.0000 5.500,0.9654,0.01559,0.00841,-0.0808,0.0152,1.0000 5.750,0.9849,0.01646,0.00933,-0.0791,0.0156,1.0000 6.000,0.9999,0.01801,0.01092,-0.0769,0.0147,1.0000 6.250,1.0195,0.01927,0.01221,-0.0753,0.0147,1.0000 6.500,1.0421,0.02025,0.01325,-0.0740,0.0154,1.0000 7.000,1.0963,0.02477,0.01810,-0.0721,0.0206,1.0000 7.250,1.1192,0.02609,0.01956,-0.0710,0.0189,1.0000 7.500,1.1409,0.02779,0.02139,-0.0699,0.0174,1.0000 7.750,1.1620,0.02981,0.02350,-0.0689,0.0163,1.0000 8.000,1.1823,0.03227,0.02606,-0.0680,0.0154,1.0000 11.750,1.1339,0.07694,0.07408,-0.0333,0.0101,1.0000 12.000,1.1136,0.08257,0.07986,-0.0353,0.0102,1.0000 12.250,1.0922,0.08911,0.08655,-0.0385,0.0103,1.0000 12.500,1.0694,0.09692,0.09450,-0.0432,0.0105,1.0000 12.750,1.0444,0.10654,0.10426,-0.0497,0.0108,1.0000