Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-eiffel10-il-100000-n5 Airfoil,eiffel10-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,29.8814 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-eiffel10-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.3907,0.11113,0.10566,-0.0095,1.0000,0.0218 -8.500,-0.3828,0.10873,0.10330,-0.0111,1.0000,0.0218 -8.000,-0.3667,0.10303,0.09769,-0.0131,1.0000,0.0221 -7.750,-0.3577,0.10017,0.09489,-0.0142,1.0000,0.0224 -7.500,-0.3471,0.09740,0.09216,-0.0159,1.0000,0.0228 -7.250,-0.3357,0.09468,0.08949,-0.0178,1.0000,0.0231 -7.000,-0.3235,0.09198,0.08684,-0.0199,1.0000,0.0236 -6.750,-0.3106,0.08931,0.08422,-0.0222,1.0000,0.0240 -6.500,-0.2968,0.08670,0.08167,-0.0247,1.0000,0.0245 -6.250,-0.2812,0.08431,0.07932,-0.0280,1.0000,0.0250 -5.750,-0.2586,0.07919,0.07434,-0.0307,1.0000,0.0259 -5.500,-0.2489,0.07694,0.07216,-0.0315,1.0000,0.0267 -5.250,-0.2384,0.07485,0.07012,-0.0326,1.0000,0.0276 -5.000,-0.2104,0.07203,0.06730,-0.0382,0.9970,0.0287 -4.750,-0.1688,0.06831,0.06355,-0.0466,0.9915,0.0293 -4.500,-0.1337,0.06444,0.05969,-0.0520,0.9849,0.0307 -4.250,-0.0595,0.06000,0.05510,-0.0672,0.9722,0.0333 -4.000,-0.0148,0.05550,0.05058,-0.0737,0.9475,0.0349 -3.750,0.0345,0.05236,0.04734,-0.0816,0.9307,0.0380 -3.500,0.0760,0.04902,0.04392,-0.0871,0.9062,0.0395 -3.250,0.1101,0.04638,0.04122,-0.0905,0.8862,0.0425 -3.000,0.1531,0.04394,0.03846,-0.0951,0.8363,0.0452 -2.750,0.1768,0.04164,0.03603,-0.0954,0.7961,0.0482 -2.500,0.2162,0.03968,0.03368,-0.0988,0.7358,0.0528 -2.000,0.2646,0.03899,0.03012,-0.1003,0.0476,0.0632 -1.750,0.3045,0.03733,0.02827,-0.1036,0.0437,0.0720 -1.500,0.3423,0.03601,0.02680,-0.1062,0.0415,0.0832 -1.000,0.4025,0.03270,0.02352,-0.1088,0.0373,0.1037 0.000,0.5488,0.02737,0.01730,-0.1137,0.0330,0.0580 0.250,0.5829,0.02625,0.01586,-0.1139,0.0328,0.0435 0.500,0.6126,0.02573,0.01519,-0.1139,0.0327,0.0421 0.750,0.6416,0.02540,0.01465,-0.1136,0.0327,0.0410 1.000,0.6700,0.02528,0.01419,-0.1130,0.0328,0.0383 1.250,0.6964,0.02528,0.01405,-0.1123,0.0330,0.0372 1.500,0.7232,0.02545,0.01405,-0.1115,0.0333,0.0362 1.750,0.7502,0.02576,0.01425,-0.1107,0.0337,0.0357 2.000,0.7775,0.02626,0.01467,-0.1100,0.0342,0.0356 2.250,0.8043,0.02694,0.01527,-0.1091,0.0349,0.0372 2.500,0.8313,0.02782,0.01608,-0.1082,0.0357,0.0395 2.750,0.8587,0.02893,0.01713,-0.1074,0.0365,0.0410 3.000,0.8862,0.03035,0.01846,-0.1068,0.0373,0.0429 3.250,0.9135,0.03172,0.01984,-0.1061,0.0375,0.0464 3.500,0.9405,0.03281,0.02114,-0.1052,0.0369,0.0582 3.750,0.9638,0.03290,0.02277,-0.1040,0.0366,1.0000 4.000,0.9898,0.03521,0.02499,-0.1033,0.0376,1.0000 4.250,1.0178,0.03663,0.02686,-0.1016,0.0425,1.0000 4.500,1.0427,0.04013,0.03023,-0.1012,0.0452,1.0000 5.000,1.1318,0.04425,0.03663,-0.0948,0.1639,1.0000 5.500,1.1694,0.05013,0.04271,-0.0929,0.1430,1.0000 6.000,1.1956,0.05635,0.04914,-0.0910,0.1121,1.0000 7.500,1.2392,0.07791,0.07189,-0.0839,0.0716,1.0000 7.750,1.2431,0.08164,0.07573,-0.0828,0.0691,1.0000 8.000,1.2512,0.08590,0.07995,-0.0821,0.0673,1.0000 8.250,1.2719,0.09525,0.08890,-0.0835,0.0655,1.0000 8.500,1.2488,0.09728,0.09147,-0.0809,0.0651,1.0000 8.750,1.2186,0.10025,0.09484,-0.0792,0.0644,1.0000 9.000,1.1936,0.10435,0.09908,-0.0783,0.0642,1.0000