Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e904-il-1000000-n5 Airfoil,e904-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,87.7053 Max Cl/Cd alpha,2.25 Url,http://airfoiltools.com/polar/csv?polar=xf-e904-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -11.250,-0.4637,0.12141,0.11970,-0.0282,1.0000,0.0037 -11.000,-0.4618,0.11782,0.11611,-0.0291,1.0000,0.0037 -10.750,-0.4604,0.11404,0.11235,-0.0301,1.0000,0.0037 -4.750,-0.2732,0.01447,0.00928,-0.0580,0.8546,0.0030 -4.500,-0.2498,0.01243,0.00697,-0.0566,0.8525,0.0025 -4.250,-0.2270,0.01090,0.00526,-0.0552,0.8506,0.0021 -4.000,-0.2048,0.00990,0.00412,-0.0539,0.8485,0.0019 -3.750,-0.1821,0.00914,0.00321,-0.0527,0.8465,0.0017 -3.500,-0.1577,0.00865,0.00260,-0.0520,0.8446,0.0016 -3.250,-0.1322,0.00835,0.00221,-0.0515,0.8429,0.0016 -3.000,-0.1061,0.00813,0.00190,-0.0512,0.8412,0.0016 -2.750,-0.0796,0.00799,0.00166,-0.0511,0.8396,0.0016 -2.500,-0.0528,0.00787,0.00148,-0.0510,0.8381,0.0019 -2.250,-0.0259,0.00775,0.00137,-0.0509,0.8367,0.0025 -2.000,0.0009,0.00766,0.00130,-0.0509,0.8349,0.0033 -1.750,0.0224,0.00700,0.00114,-0.0500,0.8324,0.1425 -1.250,0.0573,0.00531,0.00089,-0.0469,0.8275,0.5756 -1.000,0.0804,0.00501,0.00081,-0.0461,0.8246,0.6545 -0.750,0.1028,0.00470,0.00077,-0.0451,0.8206,0.7330 -0.500,0.1254,0.00453,0.00085,-0.0439,0.8158,0.8140 -0.250,0.1513,0.00455,0.00090,-0.0435,0.8110,0.8433 0.000,0.1775,0.00455,0.00093,-0.0432,0.8051,0.8582 0.250,0.2039,0.00458,0.00095,-0.0429,0.7989,0.8678 0.500,0.2304,0.00460,0.00097,-0.0427,0.7919,0.8762 0.750,0.2568,0.00463,0.00101,-0.0424,0.7865,0.8830 1.000,0.2836,0.00465,0.00105,-0.0423,0.7814,0.8898 1.250,0.3102,0.00466,0.00110,-0.0420,0.7758,0.8946 1.500,0.3371,0.00468,0.00114,-0.0420,0.7701,0.8983 1.750,0.3642,0.00470,0.00117,-0.0419,0.7626,0.9009 2.000,0.3914,0.00472,0.00127,-0.0419,0.7537,0.9027 2.250,0.4166,0.00475,0.00129,-0.0414,0.7269,0.9043 2.500,0.4296,0.00525,0.00136,-0.0383,0.6174,0.9067 2.750,0.4384,0.00613,0.00164,-0.0346,0.4657,0.9096 3.000,0.4500,0.00702,0.00193,-0.0317,0.3158,0.9125 3.250,0.4615,0.00805,0.00228,-0.0289,0.1494,0.9151 3.500,0.4744,0.00908,0.00272,-0.0263,0.0059,0.9175 3.750,0.4984,0.00934,0.00299,-0.0257,0.0021,0.9195 4.000,0.5222,0.00961,0.00340,-0.0249,0.0021,0.9215 4.250,0.5461,0.00988,0.00372,-0.0243,0.0018,0.9235 4.500,0.5699,0.01015,0.00403,-0.0237,0.0013,0.9257 4.750,0.5925,0.01057,0.00452,-0.0227,0.0010,0.9280 5.000,0.6132,0.01113,0.00519,-0.0213,0.0009,0.9304 5.250,0.6325,0.01182,0.00600,-0.0196,0.0008,0.9334 5.500,0.6507,0.01271,0.00702,-0.0177,0.0008,0.9369 5.750,0.6690,0.01410,0.00857,-0.0157,0.0008,0.9408 6.000,0.6921,0.01635,0.01105,-0.0143,0.0009,0.9436 6.250,0.7183,0.01945,0.01448,-0.0133,0.0010,0.9460 6.500,0.7388,0.02333,0.01878,-0.0108,0.0013,0.9501 6.750,0.7537,0.02661,0.02242,-0.0079,0.0015,0.9561 7.000,0.7642,0.03035,0.02653,-0.0046,0.0017,0.9644 7.500,0.7691,0.04078,0.03774,0.0017,0.0022,0.9860 7.750,0.7784,0.04472,0.04194,0.0032,0.0022,0.9960 8.000,0.7782,0.04817,0.04561,0.0062,0.0022,1.0000 8.250,0.7739,0.05123,0.04884,0.0099,0.0022,1.0000 8.500,0.7651,0.05445,0.05220,0.0137,0.0022,1.0000 8.750,0.7518,0.05705,0.05491,0.0182,0.0022,1.0000 9.000,0.7371,0.05982,0.05778,0.0219,0.0022,1.0000 9.250,0.7232,0.06282,0.06089,0.0244,0.0022,1.0000 9.500,0.7063,0.06640,0.06456,0.0258,0.0022,1.0000 9.750,0.6919,0.07035,0.06859,0.0258,0.0022,1.0000 10.000,0.6776,0.07512,0.07344,0.0243,0.0022,1.0000 10.250,0.6643,0.08120,0.07959,0.0206,0.0022,1.0000