Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e904-il-50000 Airfoil,e904-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,21.5895 Max Cl/Cd alpha,5.5 Url,http://airfoiltools.com/polar/csv?polar=xf-e904-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.4783,0.09933,0.09282,-0.0234,1.0000,0.2571 -8.250,-0.4804,0.09636,0.08994,-0.0222,1.0000,0.2701 -8.000,-0.4834,0.09349,0.08716,-0.0207,1.0000,0.2836 -7.750,-0.4939,0.09108,0.08488,-0.0188,1.0000,0.3005 -7.500,-0.5051,0.08898,0.08290,-0.0165,1.0000,0.3150 -7.250,-0.4968,0.08532,0.07930,-0.0137,1.0000,0.3347 -5.250,-0.5845,0.05332,0.04611,-0.0173,1.0000,0.1252 -5.000,-0.5709,0.04854,0.04055,-0.0155,1.0000,0.1011 -4.750,-0.5360,0.03242,0.02482,-0.0139,1.0000,0.0951 -4.500,-0.5208,0.02866,0.02038,-0.0119,1.0000,0.0873 -4.250,-0.5038,0.02496,0.01623,-0.0101,1.0000,0.0836 -4.000,-0.4838,0.02161,0.01231,-0.0083,1.0000,0.0811 -3.750,-0.4628,0.01902,0.00929,-0.0068,1.0000,0.0857 -3.500,-0.2008,0.02239,0.01434,-0.0376,1.0000,1.0000 -3.250,-0.1951,0.02214,0.01369,-0.0345,1.0000,1.0000 -3.000,-0.1883,0.02195,0.01313,-0.0316,1.0000,1.0000 -2.750,-0.1805,0.02178,0.01261,-0.0287,1.0000,1.0000 -2.500,-0.1720,0.02165,0.01218,-0.0259,1.0000,1.0000 -2.250,-0.1629,0.02154,0.01178,-0.0232,1.0000,1.0000 -2.000,-0.1533,0.02146,0.01129,-0.0205,1.0000,1.0000 -1.750,-0.1432,0.02139,0.01100,-0.0179,1.0000,1.0000 -1.500,-0.1326,0.02134,0.01073,-0.0154,1.0000,1.0000 -1.250,-0.1218,0.02131,0.01049,-0.0129,1.0000,1.0000 -1.000,-0.1105,0.02130,0.01030,-0.0104,1.0000,1.0000 -0.750,-0.0988,0.02130,0.01014,-0.0081,1.0000,1.0000 -0.500,-0.0867,0.02132,0.01000,-0.0058,1.0000,1.0000 -0.250,-0.0742,0.02136,0.00991,-0.0036,1.0000,1.0000 0.000,-0.0612,0.02143,0.00978,-0.0015,1.0000,1.0000 0.250,-0.0479,0.02151,0.00976,0.0004,1.0000,1.0000 0.500,-0.0341,0.02163,0.00978,0.0024,1.0000,1.0000 0.750,-0.0200,0.02177,0.00983,0.0042,1.0000,1.0000 1.000,-0.0054,0.02194,0.00993,0.0058,1.0000,1.0000 1.250,0.0097,0.02214,0.01009,0.0074,1.0000,1.0000 1.500,0.0251,0.02237,0.01030,0.0089,1.0000,1.0000 1.750,0.0409,0.02264,0.01056,0.0102,1.0000,1.0000 2.000,0.0570,0.02295,0.01087,0.0114,1.0000,1.0000 2.250,0.0732,0.02329,0.01122,0.0126,1.0000,1.0000 2.500,0.0895,0.02368,0.01164,0.0136,1.0000,1.0000 2.750,0.1058,0.02410,0.01212,0.0146,1.0000,1.0000 3.000,0.1221,0.02458,0.01267,0.0155,1.0000,1.0000 3.250,0.1383,0.02510,0.01328,0.0163,1.0000,1.0000 3.500,0.1543,0.02568,0.01397,0.0171,1.0000,1.0000 3.750,0.1700,0.02633,0.01486,0.0177,1.0000,1.0000 4.000,0.1853,0.02704,0.01571,0.0183,1.0000,1.0000 4.250,0.2001,0.02783,0.01667,0.0188,1.0000,1.0000 4.500,0.2144,0.02871,0.01773,0.0193,1.0000,1.0000 4.750,0.2614,0.03070,0.02009,0.0130,0.9842,1.0000 5.000,0.3336,0.03287,0.02289,0.0025,0.9478,1.0000 5.250,0.4002,0.03434,0.02525,-0.0056,0.9099,1.0000 5.500,0.6764,0.03133,0.01961,-0.0169,0.0810,1.0000 5.750,0.7198,0.03421,0.02278,-0.0181,0.0758,1.0000 6.000,0.7518,0.03798,0.02676,-0.0185,0.0710,1.0000 6.250,0.7739,0.04088,0.03009,-0.0166,0.0708,1.0000 6.500,0.7906,0.04307,0.03304,-0.0131,0.0743,1.0000 6.750,0.8040,0.04637,0.03692,-0.0099,0.0792,1.0000 7.000,0.8209,0.05091,0.04159,-0.0081,0.0835,1.0000 7.250,0.8214,0.05334,0.04493,-0.0029,0.0918,1.0000 7.500,0.8265,0.05715,0.04924,0.0005,0.1015,1.0000 7.750,0.8274,0.06139,0.05396,0.0038,0.1142,1.0000 8.000,0.8352,0.06720,0.06011,0.0055,0.1368,1.0000 8.250,0.8115,0.07107,0.06449,0.0087,0.1529,1.0000 8.500,0.7935,0.07768,0.07142,0.0085,0.1902,1.0000 8.750,0.7609,0.08113,0.07492,0.0100,0.1925,1.0000 9.000,0.7293,0.08636,0.08014,0.0084,0.2061,1.0000 9.250,0.6512,0.07828,0.07232,0.0190,0.1522,1.0000 9.500,0.6217,0.08434,0.07834,0.0162,0.1535,1.0000