Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe456-il-500000 Airfoil,goe456-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,117.943 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe456-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.3070,0.10451,0.10233,-0.0329,1.0000,0.0107 -8.750,-0.3089,0.10233,0.10018,-0.0321,1.0000,0.0113 -8.500,-0.3175,0.10117,0.09909,-0.0308,1.0000,0.0118 -8.250,-0.3094,0.09808,0.09601,-0.0332,0.9987,0.0119 -8.000,-0.2912,0.09408,0.09201,-0.0383,0.9960,0.0120 -7.000,-0.2238,0.07386,0.07182,-0.0625,0.9770,0.0130 -6.750,-0.2028,0.07119,0.06914,-0.0654,0.9738,0.0141 -6.500,-0.1752,0.06708,0.06501,-0.0725,0.9709,0.0152 -6.250,-0.1476,0.06244,0.06033,-0.0803,0.9658,0.0160 -6.000,-0.1155,0.05743,0.05527,-0.0892,0.9607,0.0170 -5.750,-0.0761,0.05177,0.04953,-0.0997,0.9567,0.0184 -5.500,-0.0392,0.04742,0.04509,-0.1070,0.9489,0.0198 -5.250,-0.0025,0.04193,0.03945,-0.1144,0.9432,0.0200 -5.000,0.0255,0.03603,0.03331,-0.1191,0.9337,0.0201 -4.750,0.0450,0.02690,0.02365,-0.1242,0.9241,0.0212 -4.500,0.0683,0.02392,0.02047,-0.1252,0.9170,0.0224 -4.250,0.0919,0.02180,0.01814,-0.1255,0.9092,0.0239 -4.000,0.1179,0.01944,0.01542,-0.1257,0.9025,0.0257 -3.750,0.1435,0.01503,0.01019,-0.1243,0.8942,0.0170 -3.500,0.1707,0.01329,0.00805,-0.1239,0.8878,0.0171 -3.250,0.1967,0.01268,0.00726,-0.1233,0.8796,0.0189 -3.000,0.2238,0.01169,0.00606,-0.1228,0.8728,0.0194 -2.750,0.2499,0.01073,0.00493,-0.1222,0.8646,0.0196 -2.500,0.2758,0.00970,0.00374,-0.1216,0.8567,0.0211 -2.250,0.3020,0.00900,0.00292,-0.1211,0.8486,0.0246 -2.000,0.3284,0.00873,0.00258,-0.1206,0.8395,0.0302 -1.750,0.3553,0.00830,0.00203,-0.1202,0.8312,0.0438 -1.500,0.3810,0.00789,0.00194,-0.1198,0.8218,0.1577 -1.250,0.4076,0.00785,0.00187,-0.1195,0.8116,0.1759 -1.000,0.4343,0.00781,0.00180,-0.1192,0.8013,0.1927 -0.750,0.4609,0.00774,0.00173,-0.1189,0.7910,0.2112 -0.500,0.4873,0.00768,0.00166,-0.1185,0.7796,0.2293 -0.250,0.5135,0.00760,0.00160,-0.1181,0.7669,0.2534 0.000,0.5392,0.00750,0.00156,-0.1177,0.7524,0.2969 0.250,0.5644,0.00734,0.00154,-0.1172,0.7363,0.3735 0.500,0.6022,0.00600,0.00159,-0.1196,0.7198,1.0000 0.750,0.6276,0.00611,0.00158,-0.1190,0.7038,1.0000 1.000,0.6530,0.00623,0.00158,-0.1184,0.6891,1.0000 1.250,0.6784,0.00635,0.00161,-0.1179,0.6751,1.0000 1.500,0.7038,0.00649,0.00165,-0.1173,0.6616,1.0000 1.750,0.7291,0.00664,0.00170,-0.1168,0.6473,1.0000 2.000,0.7544,0.00678,0.00177,-0.1162,0.6340,1.0000 2.250,0.7801,0.00692,0.00186,-0.1158,0.6235,1.0000 2.500,0.8058,0.00707,0.00198,-0.1154,0.6147,1.0000 2.750,0.8318,0.00719,0.00209,-0.1150,0.6055,1.0000 3.000,0.8573,0.00733,0.00220,-0.1145,0.5943,1.0000 3.250,0.8815,0.00751,0.00231,-0.1138,0.5752,1.0000 3.500,0.9058,0.00768,0.00245,-0.1131,0.5552,1.0000 3.750,0.9290,0.00790,0.00258,-0.1122,0.5274,1.0000 4.000,0.9522,0.00815,0.00274,-0.1112,0.4968,1.0000 4.250,0.9700,0.00874,0.00297,-0.1094,0.4170,1.0000 4.500,0.9749,0.01059,0.00380,-0.1057,0.2328,1.0000 4.750,0.9770,0.01289,0.00499,-0.1017,0.0300,1.0000 5.000,0.9987,0.01342,0.00559,-0.1005,0.0198,1.0000 5.250,1.0211,0.01387,0.00615,-0.0994,0.0184,1.0000 5.500,1.0422,0.01442,0.00680,-0.0981,0.0165,1.0000 5.750,1.0618,0.01509,0.00756,-0.0967,0.0147,1.0000 6.000,1.0794,0.01592,0.00849,-0.0948,0.0137,1.0000 6.250,1.0939,0.01698,0.00965,-0.0924,0.0129,1.0000 6.500,1.1049,0.01831,0.01107,-0.0895,0.0124,1.0000 6.750,1.1176,0.01951,0.01237,-0.0868,0.0125,1.0000 7.000,1.1327,0.02061,0.01354,-0.0845,0.0128,1.0000 7.250,1.1463,0.02243,0.01538,-0.0823,0.0123,1.0000 7.500,1.1704,0.02492,0.01789,-0.0818,0.0119,1.0000 7.750,1.1936,0.02594,0.01899,-0.0808,0.0124,1.0000 14.750,0.8772,0.15163,0.14985,-0.0804,0.0115,1.0000 15.000,0.8760,0.15656,0.15482,-0.0838,0.0117,1.0000