Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-a63a108c-il-50000 Airfoil,a63a108c-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,24.4508 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-a63a108c-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.250,-0.6237,0.09716,0.09053,0.0416,1.0000,0.3510 -7.000,-0.6211,0.09426,0.08768,0.0426,1.0000,0.3754 -6.750,-0.6204,0.09114,0.08465,0.0438,1.0000,0.4005 -6.500,-0.5981,0.08728,0.08078,0.0461,1.0000,0.4279 -6.250,-0.5978,0.08444,0.07801,0.0478,1.0000,0.4566 -5.750,-0.6169,0.05190,0.04349,-0.0105,1.0000,0.1475 -5.500,-0.5949,0.04717,0.03860,-0.0110,1.0000,0.1416 -5.250,-0.5698,0.04245,0.03299,-0.0120,1.0000,0.1317 -5.000,-0.5443,0.03861,0.02875,-0.0121,1.0000,0.1279 -4.750,-0.5172,0.03535,0.02497,-0.0121,1.0000,0.1272 -4.500,-0.4894,0.03269,0.02183,-0.0119,1.0000,0.1304 -4.250,-0.4602,0.03029,0.01888,-0.0115,1.0000,0.1332 -4.000,-0.4326,0.02797,0.01656,-0.0112,1.0000,0.1411 -3.750,-0.4036,0.02598,0.01435,-0.0106,1.0000,0.1508 -3.500,-0.3754,0.02418,0.01257,-0.0100,1.0000,0.1663 -3.250,-0.3478,0.02243,0.01099,-0.0092,1.0000,0.1911 -3.000,-0.3212,0.02047,0.00937,-0.0084,1.0000,0.2415 -2.750,-0.3184,0.01656,0.00861,-0.0011,1.0000,0.6929 -2.500,-0.1880,0.01757,0.00895,-0.0095,1.0000,1.0000 -2.250,-0.1682,0.01699,0.00814,-0.0097,1.0000,1.0000 -2.000,-0.1484,0.01650,0.00746,-0.0096,1.0000,1.0000 -1.750,-0.1288,0.01610,0.00689,-0.0093,1.0000,1.0000 -1.500,-0.1096,0.01579,0.00643,-0.0087,1.0000,1.0000 -1.250,-0.0906,0.01555,0.00604,-0.0079,1.0000,1.0000 -1.000,-0.0715,0.01537,0.00575,-0.0070,1.0000,1.0000 -0.750,-0.0526,0.01526,0.00553,-0.0060,1.0000,1.0000 -0.500,-0.0337,0.01521,0.00538,-0.0049,1.0000,1.0000 -0.250,-0.0149,0.01521,0.00529,-0.0038,1.0000,1.0000 0.000,0.0040,0.01525,0.00527,-0.0026,1.0000,1.0000 0.250,0.0230,0.01534,0.00530,-0.0014,1.0000,1.0000 0.500,0.0425,0.01546,0.00539,-0.0004,1.0000,1.0000 0.750,0.0624,0.01562,0.00553,0.0006,1.0000,1.0000 1.000,0.0826,0.01581,0.00572,0.0014,1.0000,1.0000 1.250,0.1032,0.01605,0.00598,0.0021,1.0000,1.0000 1.500,0.1241,0.01633,0.00630,0.0026,1.0000,1.0000 1.750,0.1452,0.01666,0.00669,0.0030,1.0000,1.0000 2.000,0.1662,0.01705,0.00716,0.0033,1.0000,1.0000 2.250,0.1870,0.01751,0.00772,0.0035,1.0000,1.0000 2.500,0.2074,0.01806,0.00839,0.0034,1.0000,1.0000 2.750,0.2271,0.01873,0.00923,0.0032,1.0000,1.0000 3.000,0.3686,0.01876,0.01004,-0.0172,0.9285,1.0000 3.250,0.4203,0.01799,0.00965,-0.0159,0.8238,1.0000 3.500,0.4296,0.01757,0.00891,-0.0066,0.6744,1.0000 3.750,0.4391,0.01888,0.00880,0.0003,0.4758,1.0000 4.000,0.4601,0.02076,0.00977,0.0022,0.3711,1.0000 4.250,0.4854,0.02241,0.01107,0.0031,0.3102,1.0000 4.500,0.5117,0.02402,0.01249,0.0038,0.2693,1.0000 4.750,0.5379,0.02574,0.01398,0.0045,0.2403,1.0000 5.000,0.5653,0.02749,0.01588,0.0048,0.2169,1.0000 5.250,0.5923,0.02943,0.01797,0.0052,0.1989,1.0000 5.500,0.6189,0.03159,0.02027,0.0054,0.1847,1.0000 5.750,0.6447,0.03389,0.02256,0.0057,0.1731,1.0000 6.000,0.6709,0.03672,0.02608,0.0056,0.1644,1.0000 6.250,0.6951,0.03952,0.02885,0.0058,0.1571,1.0000 6.500,0.7175,0.04339,0.03358,0.0054,0.1532,1.0000 6.750,0.7373,0.04785,0.03863,0.0048,0.1517,1.0000 7.000,0.7535,0.05289,0.04419,0.0038,0.1520,1.0000 7.250,0.7667,0.05833,0.05003,0.0026,0.1539,1.0000 7.500,0.7824,0.06354,0.05542,0.0020,0.1582,1.0000 7.750,0.6941,0.09751,0.09035,-0.0464,0.3886,1.0000 8.000,0.7046,0.10145,0.09427,-0.0453,0.3702,1.0000