Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-v13006-il-50000 Airfoil,v13006-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,27.9159 Max Cl/Cd alpha,4.5 Url,http://www.airfoiltools.com/polar/csv?polar=xf-v13006-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6283,0.10634,0.09956,0.0273,1.0000,0.2248 -8.000,-0.6300,0.10300,0.09630,0.0261,1.0000,0.2360 -7.750,-0.6469,0.10116,0.09459,0.0221,1.0000,0.2469 -7.500,-0.6196,0.09592,0.08931,0.0269,1.0000,0.2678 -7.250,-0.6211,0.09301,0.08647,0.0267,1.0000,0.2878 -7.000,-0.6106,0.08939,0.08289,0.0289,1.0000,0.3135 -6.750,-0.6042,0.08620,0.07975,0.0309,1.0000,0.3425 -6.500,-0.6047,0.08358,0.07717,0.0322,1.0000,0.3757 -6.250,-0.5857,0.08003,0.07363,0.0371,1.0000,0.4158 -6.000,-0.5805,0.07756,0.07122,0.0411,1.0000,0.4626 -5.750,-0.5463,0.07355,0.06717,0.0470,1.0000,0.5274 -5.500,-0.5177,0.07023,0.06383,0.0525,1.0000,0.6056 -5.250,-0.4607,0.06515,0.05861,0.0563,1.0000,0.7181 -4.500,-0.4582,0.04213,0.03361,-0.0147,1.0000,0.1865 -4.250,-0.4231,0.03818,0.02857,-0.0157,1.0000,0.1450 -4.000,-0.3965,0.03468,0.02473,-0.0154,1.0000,0.1348 -3.750,-0.3682,0.03239,0.02181,-0.0147,1.0000,0.1300 -3.500,-0.3412,0.02984,0.01893,-0.0141,1.0000,0.1279 -3.250,-0.3131,0.02757,0.01632,-0.0134,1.0000,0.1251 -3.000,-0.2847,0.02561,0.01404,-0.0125,1.0000,0.1246 -2.750,-0.2565,0.02400,0.01216,-0.0116,1.0000,0.1292 -2.500,-0.2286,0.02231,0.01048,-0.0108,1.0000,0.1388 -2.250,-0.1995,0.02084,0.00890,-0.0099,1.0000,0.1490 -2.000,-0.1739,0.01950,0.00760,-0.0089,1.0000,0.1743 -1.750,-0.1057,0.01453,0.00554,-0.0125,1.0000,1.0000 -1.500,-0.0838,0.01443,0.00500,-0.0113,1.0000,1.0000 -1.250,-0.0622,0.01436,0.00459,-0.0102,1.0000,1.0000 -1.000,-0.0405,0.01431,0.00430,-0.0092,1.0000,1.0000 -0.750,-0.0189,0.01427,0.00408,-0.0081,1.0000,1.0000 -0.500,0.0028,0.01426,0.00391,-0.0070,1.0000,1.0000 -0.250,0.0244,0.01426,0.00379,-0.0060,1.0000,1.0000 0.000,0.0460,0.01429,0.00373,-0.0050,1.0000,1.0000 0.250,0.0676,0.01433,0.00371,-0.0040,1.0000,1.0000 0.500,0.0893,0.01439,0.00375,-0.0031,1.0000,1.0000 0.750,0.1109,0.01448,0.00384,-0.0022,1.0000,1.0000 1.000,0.1324,0.01460,0.00397,-0.0014,1.0000,1.0000 1.250,0.1538,0.01475,0.00417,-0.0006,1.0000,1.0000 1.500,0.1748,0.01494,0.00443,0.0001,1.0000,1.0000 1.750,0.1957,0.01519,0.00477,0.0007,1.0000,1.0000 2.000,0.2160,0.01551,0.00521,0.0012,1.0000,1.0000 2.250,0.2356,0.01593,0.00576,0.0015,1.0000,1.0000 2.500,0.2537,0.01652,0.00650,0.0014,1.0000,1.0000 2.750,0.2854,0.01740,0.00761,-0.0021,0.9907,1.0000 3.000,0.4233,0.01746,0.00855,-0.0220,0.8948,1.0000 3.250,0.4725,0.01728,0.00859,-0.0220,0.7971,1.0000 3.500,0.4934,0.01770,0.00880,-0.0175,0.7108,1.0000 3.750,0.5133,0.01846,0.00930,-0.0140,0.6367,1.0000 4.000,0.5351,0.01934,0.01003,-0.0115,0.5746,1.0000 4.250,0.5550,0.02006,0.01055,-0.0087,0.5125,1.0000 4.500,0.5706,0.02044,0.01057,-0.0052,0.4341,1.0000 4.750,0.5870,0.02127,0.01106,-0.0025,0.3367,1.0000 5.000,0.6009,0.02383,0.01242,0.0001,0.1765,1.0000 5.250,0.6250,0.02582,0.01418,0.0013,0.1371,1.0000 5.500,0.6509,0.02797,0.01623,0.0023,0.1222,1.0000 5.750,0.6780,0.03034,0.01907,0.0032,0.1146,1.0000 6.000,0.7029,0.03289,0.02167,0.0039,0.1086,1.0000 6.250,0.7268,0.03578,0.02524,0.0047,0.1043,1.0000 6.500,0.7488,0.03908,0.02906,0.0054,0.1019,1.0000 6.750,0.7681,0.04332,0.03391,0.0060,0.1029,1.0000 7.000,0.7840,0.04811,0.03927,0.0062,0.1051,1.0000 7.250,0.7986,0.05298,0.04451,0.0062,0.1077,1.0000 7.500,0.7998,0.06072,0.05311,0.0039,0.1155,1.0000 7.750,0.8095,0.06639,0.05893,0.0032,0.1210,1.0000 8.000,0.7073,0.06429,0.05769,0.0026,0.1285,1.0000 8.250,0.6999,0.07115,0.06461,0.0005,0.1375,1.0000