Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-kenmar-il-100000-n5 Airfoil,kenmar-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,4.65854 Max Cl/Cd alpha,-8.5 Url,http://airfoiltools.com/polar/csv?polar=xf-kenmar-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -11.750,0.4078,0.13213,0.12291,-0.1437,0.4851,0.0951 -11.500,0.4164,0.13019,0.12099,-0.1446,0.4847,0.0965 -11.250,0.4223,0.12824,0.11907,-0.1457,0.4844,0.0981 -11.000,0.4201,0.12637,0.11722,-0.1473,0.4842,0.0996 -10.750,0.4193,0.12437,0.11526,-0.1486,0.4839,0.0999 -10.250,0.4230,0.11982,0.11078,-0.1510,0.4833,0.1002 -9.750,0.4314,0.10968,0.10062,-0.1533,0.4827,0.0749 -9.500,0.4436,0.10814,0.09915,-0.1531,0.4822,0.0743 -9.250,0.4519,0.10620,0.09728,-0.1533,0.4818,0.0735 -9.000,0.4570,0.10394,0.09508,-0.1537,0.4813,0.0727 -8.750,0.4593,0.10137,0.09257,-0.1543,0.4809,0.0718 -8.500,0.4584,0.09840,0.08967,-0.1550,0.4806,0.0709 -8.000,0.2893,0.06675,0.05772,-0.1723,0.4814,0.0677 -7.750,0.2482,0.06198,0.05283,-0.1733,0.4813,0.0676 -7.500,0.2169,0.05902,0.04977,-0.1722,0.4811,0.0676 -7.250,0.1888,0.05721,0.04789,-0.1695,0.4809,0.0676 -7.000,0.1618,0.05629,0.04692,-0.1653,0.4806,0.0676 -6.750,0.1379,0.05547,0.04605,-0.1614,0.4803,0.0677 -6.500,0.1201,0.05466,0.04518,-0.1581,0.4799,0.0678 -6.250,0.1064,0.05400,0.04444,-0.1548,0.4795,0.0679 -6.000,0.0950,0.05354,0.04391,-0.1513,0.4790,0.0680 -5.750,0.0861,0.05339,0.04379,-0.1474,0.4783,0.0681 -5.500,0.0744,0.05344,0.04387,-0.1430,0.4773,0.0682 -5.250,0.0583,0.05372,0.04421,-0.1379,0.4760,0.0683 -5.000,0.0339,0.05437,0.04494,-0.1318,0.4747,0.0684 -4.750,-0.0249,0.05624,0.04697,-0.1212,0.4733,0.0682 -4.500,-0.1124,0.06128,0.05240,-0.1096,0.4703,0.0677 -4.250,-0.1344,0.06342,0.05455,-0.1071,0.4677,0.0677 -4.000,-0.1352,0.06444,0.05543,-0.1068,0.4660,0.0679 -3.750,-0.1275,0.06514,0.05605,-0.1070,0.4647,0.0682 -3.500,-0.1119,0.06537,0.05622,-0.1072,0.4638,0.0685 -3.250,-0.0923,0.06542,0.05621,-0.1076,0.4631,0.0690 -3.000,-0.1654,0.07355,0.06450,-0.1059,0.4566,0.0685 -2.750,-0.1785,0.07636,0.06732,-0.1057,0.4536,0.0686 -2.500,-0.1737,0.07779,0.06874,-0.1060,0.4517,0.0688 -2.250,-0.1638,0.07890,0.06983,-0.1064,0.4501,0.0692 -2.000,-0.1499,0.07977,0.07066,-0.1068,0.4486,0.0697 -1.750,-0.1310,0.08029,0.07113,-0.1074,0.4471,0.0702 -1.500,-0.1088,0.08063,0.07140,-0.1079,0.4457,0.0709 -1.250,-0.0852,0.08094,0.07162,-0.1085,0.4446,0.0717 -1.000,-0.0607,0.08125,0.07186,-0.1090,0.4436,0.0725 -0.750,-0.0362,0.08168,0.07220,-0.1094,0.4429,0.0734 -0.500,-0.0104,0.08216,0.07256,-0.1099,0.4422,0.0746 -0.250,0.0151,0.08265,0.07308,-0.1103,0.4416,0.0759 0.250,-0.0211,0.08965,0.08024,-0.1104,0.4337,0.0762 0.500,-0.0090,0.09110,0.08174,-0.1108,0.4319,0.0772 0.750,0.0058,0.09246,0.08313,-0.1113,0.4304,0.0785 1.000,0.0227,0.09371,0.08438,-0.1118,0.4292,0.0799 1.250,0.0418,0.09487,0.08552,-0.1123,0.4280,0.0813 1.750,0.0919,0.09650,0.08719,-0.1137,0.4255,0.0844 2.000,0.1209,0.09725,0.08798,-0.1146,0.4246,0.0865 2.250,0.1516,0.09801,0.08872,-0.1156,0.4238,0.0892 2.500,0.1836,0.09883,0.08954,-0.1167,0.4232,0.0924 3.000,0.1537,0.10525,0.09615,-0.1174,0.4142,0.0935 3.250,0.1753,0.10654,0.09747,-0.1184,0.4122,0.0978 3.500,0.1987,0.10788,0.09886,-0.1196,0.4108,0.1030 3.750,0.2239,0.10917,0.10019,-0.1207,0.4097,0.1107 4.000,0.2527,0.11043,0.10153,-0.1223,0.4088,0.1224 5.000,0.3380,0.11968,0.11276,-0.1355,0.3976,0.4488 5.250,0.3332,0.12016,0.11371,-0.1293,0.3963,0.5486 5.500,0.3520,0.12152,0.11504,-0.1288,0.3951,0.6004 5.750,0.3810,0.12317,0.11654,-0.1303,0.3941,0.6334 6.250,0.3785,0.12758,0.12100,-0.1283,0.3862,0.6604 6.500,0.3858,0.12899,0.12240,-0.1261,0.3843,0.6822 6.750,0.3847,0.12951,0.12295,-0.1209,0.3829,0.6977 7.000,0.3888,0.13006,0.12349,-0.1167,0.3817,0.7141 7.250,0.4025,0.13078,0.12416,-0.1142,0.3807,0.7300