Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e58-il-200000 Airfoil,e58-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,108.161 Max Cl/Cd alpha,4.5 Url,http://airfoiltools.com/polar/csv?polar=xf-e58-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -6.500,-0.4085,0.10751,0.10447,-0.0082,1.0000,0.0255 -6.250,-0.4142,0.10572,0.10272,-0.0063,1.0000,0.0260 -6.000,-0.4176,0.10381,0.10084,-0.0052,1.0000,0.0262 -5.750,-0.4175,0.10148,0.09851,-0.0050,1.0000,0.0268 -5.500,-0.4159,0.09898,0.09604,-0.0053,1.0000,0.0274 -5.250,-0.4123,0.09634,0.09342,-0.0062,1.0000,0.0280 -5.000,-0.4066,0.09349,0.09059,-0.0077,1.0000,0.0288 -4.750,-0.3980,0.09047,0.08758,-0.0100,1.0000,0.0296 -4.500,-0.3860,0.08724,0.08436,-0.0132,1.0000,0.0306 -4.250,-0.3629,0.08346,0.08057,-0.0198,0.9996,0.0322 -4.000,-0.2767,0.07711,0.07406,-0.0452,0.9945,0.0340 -3.750,-0.2081,0.06737,0.06423,-0.0621,0.9792,0.0356 -3.500,-0.1779,0.06416,0.06100,-0.0655,0.9738,0.0379 -3.250,-0.0662,0.05474,0.05121,-0.0949,0.9722,0.0480 -3.000,-0.0509,0.05279,0.04931,-0.0937,0.9653,0.0508 -2.750,0.0339,0.04609,0.04226,-0.1122,0.9644,0.0623 -2.500,0.0971,0.04202,0.03791,-0.1232,0.9627,0.0755 -2.000,0.2830,0.02691,0.02058,-0.1541,0.9718,0.0502 -1.750,0.3209,0.02564,0.01901,-0.1564,0.9677,0.0537 -1.500,0.3601,0.02467,0.01771,-0.1587,0.9650,0.0567 -1.250,0.3994,0.02410,0.01692,-0.1610,0.9624,0.0599 -1.000,0.4430,0.02345,0.01624,-0.1643,0.9602,0.0669 -0.750,0.4816,0.02321,0.01594,-0.1665,0.9558,0.0726 -0.500,0.5177,0.02291,0.01568,-0.1683,0.9502,0.0853 -0.250,0.5617,0.02270,0.01572,-0.1715,0.9469,0.1685 0.000,0.5940,0.02266,0.01574,-0.1725,0.9400,0.2130 0.250,0.6339,0.02251,0.01567,-0.1749,0.9351,0.2484 0.500,0.6831,0.02216,0.01555,-0.1791,0.9323,0.3122 0.750,0.7061,0.02068,0.01551,-0.1778,0.9234,1.0000 1.000,0.7546,0.02038,0.01505,-0.1814,0.9197,1.0000 1.250,0.7828,0.02028,0.01488,-0.1813,0.9108,1.0000 1.500,0.8243,0.02006,0.01462,-0.1838,0.9075,1.0000 1.750,0.8533,0.02001,0.01455,-0.1839,0.9002,1.0000 2.000,0.8914,0.01974,0.01428,-0.1856,0.8957,1.0000 2.250,0.9380,0.01916,0.01372,-0.1888,0.8929,1.0000 2.500,0.9661,0.01883,0.01346,-0.1884,0.8829,1.0000 2.750,1.0114,0.01814,0.01282,-0.1912,0.8799,1.0000 3.000,1.0372,0.01792,0.01267,-0.1904,0.8701,1.0000 3.250,1.0840,0.01694,0.01179,-0.1932,0.8665,1.0000 3.500,1.1169,0.01604,0.01102,-0.1932,0.8547,1.0000 3.750,1.1489,0.01515,0.01023,-0.1929,0.8421,1.0000 4.000,1.1795,0.01442,0.00961,-0.1924,0.8273,1.0000 4.250,1.2047,0.01405,0.00936,-0.1912,0.8070,1.0000 4.500,1.3001,0.01202,0.00662,-0.2019,0.6446,1.0000 4.750,1.3130,0.01319,0.00719,-0.1985,0.5439,1.0000 5.000,1.3180,0.01449,0.00793,-0.1939,0.4500,1.0000 5.250,1.3231,0.01589,0.00880,-0.1896,0.3602,1.0000 5.500,1.3286,0.01740,0.00970,-0.1856,0.2642,1.0000 5.750,1.3374,0.01908,0.01080,-0.1824,0.1633,1.0000 6.000,1.3429,0.02169,0.01260,-0.1787,0.0501,1.0000 6.250,1.3589,0.02303,0.01392,-0.1763,0.0352,1.0000 6.500,1.3750,0.02419,0.01512,-0.1741,0.0294,1.0000 6.750,1.3865,0.02586,0.01691,-0.1711,0.0272,1.0000 7.000,1.4005,0.02735,0.01854,-0.1684,0.0260,1.0000 7.250,1.4159,0.02910,0.02041,-0.1661,0.0249,1.0000 7.500,1.4359,0.03111,0.02257,-0.1645,0.0241,1.0000 7.750,1.4580,0.03287,0.02444,-0.1634,0.0223,1.0000 8.000,1.4853,0.03519,0.02685,-0.1634,0.0207,1.0000