Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e376-il-500000 Airfoil,e376-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,134.976 Max Cl/Cd alpha,7 Url,http://airfoiltools.com/polar/csv?polar=xf-e376-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -1.250,0.4602,0.03307,0.02873,-0.0991,0.5722,0.0114 -1.000,0.4939,0.03143,0.02700,-0.1014,0.5673,0.0126 -0.750,0.5283,0.02984,0.02532,-0.1036,0.5619,0.0133 -0.500,0.5633,0.02858,0.02392,-0.1055,0.5572,0.0141 -0.250,0.6006,0.02781,0.02304,-0.1073,0.5523,0.0146 0.000,0.6348,0.02668,0.02182,-0.1088,0.5475,0.0148 0.250,0.6675,0.02542,0.02040,-0.1100,0.5430,0.0149 0.500,0.6991,0.02288,0.01778,-0.1118,0.5386,0.0156 0.750,0.7278,0.02155,0.01640,-0.1128,0.5337,0.0167 1.000,0.7584,0.02055,0.01527,-0.1136,0.5295,0.0181 1.250,0.7902,0.01960,0.01421,-0.1142,0.5251,0.0205 1.500,0.8241,0.01942,0.01391,-0.1142,0.5203,0.0228 2.500,0.9441,0.01519,0.00920,-0.1157,0.5028,0.0355 2.750,0.9720,0.01462,0.00852,-0.1158,0.4986,0.0374 3.000,1.0009,0.01397,0.00781,-0.1158,0.4940,0.0393 3.250,1.0334,0.01179,0.00522,-0.1153,0.4900,0.0224 3.500,1.0610,0.01086,0.00400,-0.1150,0.4859,0.0215 3.750,1.0880,0.01049,0.00356,-0.1147,0.4812,0.0229 4.250,1.1414,0.01040,0.00343,-0.1142,0.4706,0.0653 4.500,1.1682,0.01049,0.00359,-0.1140,0.4645,0.0812 4.750,1.1948,0.01052,0.00361,-0.1138,0.4591,0.0898 5.000,1.2214,0.01057,0.00373,-0.1136,0.4536,0.1005 5.250,1.2479,0.01062,0.00381,-0.1134,0.4472,0.1180 5.500,1.2743,0.01072,0.00395,-0.1132,0.4408,0.1401 5.750,1.3007,0.01079,0.00409,-0.1131,0.4339,0.1626 6.000,1.3268,0.01092,0.00424,-0.1128,0.4275,0.1848 6.250,1.3532,0.01097,0.00444,-0.1127,0.4199,0.2152 6.500,1.3804,0.01028,0.00465,-0.1129,0.4123,1.0000 6.750,1.4063,0.01044,0.00481,-0.1126,0.4034,1.0000 7.000,1.4321,0.01061,0.00501,-0.1124,0.3942,1.0000 7.250,1.4575,0.01081,0.00522,-0.1121,0.3843,1.0000 7.500,1.4826,0.01103,0.00544,-0.1118,0.3668,1.0000 7.750,1.5059,0.01149,0.00578,-0.1114,0.3293,1.0000 8.000,1.5283,0.01213,0.00624,-0.1109,0.2883,1.0000 8.250,1.5484,0.01314,0.00696,-0.1102,0.2351,1.0000 8.500,1.5649,0.01463,0.00804,-0.1093,0.1697,1.0000 8.750,1.5805,0.01617,0.00921,-0.1083,0.1141,1.0000 9.000,1.5937,0.01789,0.01059,-0.1069,0.0623,1.0000 9.250,1.6013,0.02012,0.01245,-0.1049,0.0141,1.0000 9.500,1.6159,0.02137,0.01372,-0.1034,0.0078,1.0000 9.750,1.6318,0.02235,0.01485,-0.1020,0.0070,1.0000 10.000,1.6452,0.02348,0.01612,-0.1004,0.0064,1.0000 10.250,1.6553,0.02478,0.01756,-0.0984,0.0060,1.0000 10.500,1.6592,0.02629,0.01920,-0.0957,0.0056,1.0000 10.750,1.6564,0.02800,0.02106,-0.0924,0.0054,1.0000 11.000,1.6499,0.03037,0.02361,-0.0897,0.0052,1.0000 11.250,1.6451,0.03304,0.02643,-0.0881,0.0051,1.0000 11.500,1.6380,0.03631,0.02986,-0.0869,0.0050,1.0000 11.750,1.6302,0.03997,0.03367,-0.0862,0.0049,1.0000 12.000,1.6228,0.04378,0.03763,-0.0858,0.0049,1.0000 12.250,1.6174,0.04744,0.04142,-0.0855,0.0049,1.0000 12.500,1.6094,0.05152,0.04565,-0.0853,0.0049,1.0000 12.750,1.6039,0.05534,0.04960,-0.0852,0.0049,1.0000 13.000,1.5984,0.05920,0.05358,-0.0851,0.0049,1.0000 13.250,1.5932,0.06308,0.05760,-0.0849,0.0049,1.0000 13.500,1.5894,0.06684,0.06148,-0.0849,0.0050,1.0000 13.750,1.5860,0.07065,0.06543,-0.0848,0.0050,1.0000 14.000,1.5838,0.07441,0.06934,-0.0849,0.0051,1.0000 14.250,1.5810,0.07835,0.07346,-0.0849,0.0053,1.0000 14.500,1.5776,0.08257,0.07790,-0.0846,0.0055,1.0000 14.750,1.5713,0.08747,0.08307,-0.0843,0.0059,1.0000 15.000,1.5613,0.09332,0.08920,-0.0847,0.0063,1.0000 15.250,1.5487,0.09977,0.09591,-0.0862,0.0067,1.0000 15.500,1.5344,0.10667,0.10303,-0.0885,0.0069,1.0000 15.750,1.5192,0.11399,0.11057,-0.0915,0.0071,1.0000