Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e58-il-500000 Airfoil,e58-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,175.109 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-e58-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.250,-0.1845,0.09231,0.09000,-0.0726,0.9599,0.0156 -7.000,-0.1698,0.08946,0.08715,-0.0764,0.9586,0.0157 -6.750,-0.1854,0.08853,0.08626,-0.0713,0.9508,0.0158 -6.500,-0.1689,0.08504,0.08277,-0.0754,0.9484,0.0158 -6.250,-0.1476,0.08096,0.07868,-0.0809,0.9469,0.0159 -6.000,-0.1228,0.07695,0.07466,-0.0870,0.9458,0.0159 -5.750,-0.1330,0.07553,0.07327,-0.0836,0.9380,0.0159 -5.500,-0.1246,0.07030,0.06806,-0.0858,0.9359,0.0167 -5.250,-0.1003,0.06698,0.06472,-0.0903,0.9345,0.0171 -5.000,-0.0709,0.06339,0.06111,-0.0963,0.9335,0.0178 -4.750,-0.0603,0.06082,0.05854,-0.0980,0.9279,0.0183 -4.500,-0.0279,0.05673,0.05439,-0.1053,0.9245,0.0195 -4.250,0.0381,0.05083,0.04838,-0.1213,0.9233,0.0229 -3.250,0.3460,0.02017,0.01555,-0.1858,0.9329,0.0235 -3.000,0.3922,0.01735,0.01233,-0.1910,0.9332,0.0273 -2.750,0.4335,0.01635,0.01114,-0.1939,0.9329,0.0303 -2.500,0.4568,0.01585,0.01051,-0.1930,0.9282,0.0322 -2.250,0.4939,0.01497,0.00948,-0.1949,0.9258,0.0360 -2.000,0.5345,0.01410,0.00854,-0.1976,0.9244,0.0391 -1.750,0.5737,0.01354,0.00795,-0.1999,0.9232,0.0428 -1.500,0.6159,0.01293,0.00730,-0.2027,0.9221,0.0461 -1.250,0.6574,0.01240,0.00671,-0.2054,0.9212,0.0486 -1.000,0.6989,0.01190,0.00622,-0.2081,0.9205,0.0566 -0.750,0.7398,0.01140,0.00596,-0.2109,0.9201,0.1427 -0.500,0.7792,0.01107,0.00571,-0.2133,0.9196,0.1740 -0.250,0.7919,0.01121,0.00588,-0.2101,0.9125,0.1866 0.000,0.8302,0.01080,0.00556,-0.2122,0.9111,0.2098 0.500,0.9166,0.00922,0.00505,-0.2190,0.9088,0.6416 0.750,0.9450,0.00826,0.00470,-0.2185,0.9069,1.0000 1.000,0.9699,0.00822,0.00464,-0.2177,0.9018,1.0000 1.250,0.9997,0.00807,0.00448,-0.2179,0.8976,1.0000 1.500,1.0354,0.00776,0.00417,-0.2193,0.8945,1.0000 1.750,1.0617,0.00759,0.00402,-0.2187,0.8866,1.0000 2.000,1.0951,0.00723,0.00365,-0.2195,0.8775,1.0000 2.250,1.1213,0.00714,0.00358,-0.2189,0.8677,1.0000 2.500,1.1476,0.00707,0.00352,-0.2183,0.8554,1.0000 2.750,1.1755,0.00695,0.00341,-0.2180,0.8340,1.0000 3.000,1.2065,0.00689,0.00316,-0.2182,0.7822,1.0000 3.250,1.2146,0.00804,0.00344,-0.2135,0.6373,1.0000 3.500,1.2212,0.00919,0.00402,-0.2090,0.5366,1.0000 3.750,1.2318,0.01022,0.00457,-0.2056,0.4477,1.0000 4.000,1.2478,0.01105,0.00507,-0.2034,0.3847,1.0000 4.250,1.2625,0.01212,0.00565,-0.2010,0.2909,1.0000 4.500,1.2805,0.01298,0.00621,-0.1993,0.2348,1.0000 4.750,1.2981,0.01396,0.00679,-0.1976,0.1644,1.0000 5.000,1.3144,0.01515,0.00751,-0.1957,0.0841,1.0000 5.250,1.3304,0.01645,0.00842,-0.1936,0.0256,1.0000 5.500,1.3509,0.01718,0.00918,-0.1920,0.0184,1.0000 5.750,1.3714,0.01784,0.00995,-0.1906,0.0166,1.0000 6.000,1.3908,0.01863,0.01083,-0.1889,0.0152,1.0000 6.250,1.4084,0.01963,0.01193,-0.1868,0.0139,1.0000 6.500,1.4200,0.02133,0.01379,-0.1836,0.0124,1.0000 6.750,1.4354,0.02255,0.01511,-0.1813,0.0119,1.0000 7.000,1.4524,0.02360,0.01629,-0.1792,0.0115,1.0000 7.250,1.4690,0.02487,0.01767,-0.1771,0.0111,1.0000 7.500,1.4865,0.02638,0.01931,-0.1751,0.0106,1.0000 7.750,1.5065,0.02818,0.02125,-0.1736,0.0103,1.0000 8.000,1.5331,0.03060,0.02385,-0.1733,0.0102,1.0000 8.250,1.5666,0.03415,0.02769,-0.1740,0.0105,1.0000