Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e850-il-500000 Airfoil,e850-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,97.465 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-e850-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.4439,0.08243,0.08037,-0.0314,1.0000,0.0124 -8.750,-0.4509,0.07837,0.07634,-0.0315,1.0000,0.0125 -8.500,-0.4579,0.07485,0.07285,-0.0312,1.0000,0.0128 -8.250,-0.4684,0.07064,0.06867,-0.0314,1.0000,0.0127 -8.000,-0.4816,0.06628,0.06434,-0.0318,1.0000,0.0127 -7.750,-0.5046,0.05978,0.05786,-0.0350,1.0000,0.0122 -7.500,-0.5307,0.05718,0.05523,-0.0345,1.0000,0.0118 -7.250,-0.5313,0.05034,0.04824,-0.0419,0.9967,0.0119 -7.000,-0.5258,0.04384,0.04156,-0.0472,0.9940,0.0122 -6.750,-0.5178,0.03902,0.03660,-0.0499,0.9909,0.0127 -6.500,-0.5056,0.03468,0.03209,-0.0521,0.9879,0.0134 -6.250,-0.4890,0.03041,0.02761,-0.0543,0.9854,0.0143 -6.000,-0.4679,0.02629,0.02324,-0.0566,0.9836,0.0155 -5.750,-0.4432,0.02226,0.01890,-0.0586,0.9822,0.0172 -5.500,-0.4142,0.01903,0.01532,-0.0600,0.9811,0.0199 -5.250,-0.3903,0.01998,0.01595,-0.0583,0.9773,0.0220 -5.000,-0.3733,0.01315,0.00853,-0.0594,0.9751,0.0238 -4.750,-0.3474,0.01059,0.00582,-0.0602,0.9736,0.0260 -4.500,-0.3186,0.00871,0.00371,-0.0607,0.9723,0.0284 -4.250,-0.3122,0.01860,0.01305,-0.0588,0.9737,0.0195 -4.000,-0.2815,0.01581,0.00994,-0.0578,0.9731,0.0096 -3.750,-0.2524,0.01387,0.00781,-0.0577,0.9722,0.0080 -3.500,-0.2214,0.01259,0.00635,-0.0583,0.9712,0.0070 -3.250,-0.1886,0.01182,0.00539,-0.0593,0.9702,0.0065 -3.000,-0.1550,0.01144,0.00484,-0.0605,0.9693,0.0065 -2.750,-0.1229,0.01125,0.00448,-0.0614,0.9679,0.0076 -2.500,-0.1004,0.01109,0.00421,-0.0603,0.9640,0.0093 -2.250,-0.0724,0.00975,0.00388,-0.0615,0.9622,0.2791 -2.000,-0.0430,0.00906,0.00390,-0.0626,0.9605,0.4811 -1.750,-0.0121,0.00886,0.00412,-0.0634,0.9589,0.5970 -1.500,0.0213,0.00885,0.00416,-0.0647,0.9576,0.6261 -1.250,0.0559,0.00882,0.00416,-0.0663,0.9565,0.6391 -1.000,0.0829,0.00878,0.00413,-0.0662,0.9531,0.6489 -0.750,0.1117,0.00871,0.00409,-0.0665,0.9495,0.6588 -0.500,0.1459,0.00861,0.00402,-0.0680,0.9473,0.6694 -0.250,0.1820,0.00850,0.00395,-0.0698,0.9455,0.6807 0.000,0.2202,0.00835,0.00386,-0.0721,0.9441,0.6927 0.250,0.2610,0.00815,0.00373,-0.0749,0.9430,0.7054 0.500,0.2851,0.00802,0.00368,-0.0740,0.9363,0.7187 0.750,0.3268,0.00771,0.00348,-0.0769,0.9339,0.7332 1.000,0.3751,0.00726,0.00315,-0.0810,0.9317,0.7486 1.250,0.4116,0.00685,0.00286,-0.0824,0.9238,0.7656 1.500,0.4507,0.00637,0.00258,-0.0842,0.9124,0.7840 1.750,0.4820,0.00611,0.00246,-0.0846,0.9002,0.8044 2.000,0.5097,0.00589,0.00237,-0.0840,0.8812,0.8277 2.250,0.5350,0.00571,0.00226,-0.0829,0.8435,0.8551 2.500,0.5575,0.00572,0.00217,-0.0810,0.7692,0.8891 2.750,0.5631,0.00660,0.00232,-0.0757,0.5790,0.9482 3.000,0.5738,0.00838,0.00283,-0.0730,0.2924,1.0000 3.250,0.5880,0.00979,0.00335,-0.0709,0.0947,1.0000 3.500,0.6058,0.01117,0.00444,-0.0688,0.0132,1.0000 3.750,0.6279,0.01208,0.00549,-0.0673,0.0113,1.0000 4.000,0.6495,0.01314,0.00665,-0.0658,0.0104,1.0000 4.250,0.6731,0.01382,0.00734,-0.0651,0.0069,1.0000 4.500,0.6940,0.01680,0.01056,-0.0633,0.0057,1.0000 4.750,0.7201,0.01750,0.01137,-0.0628,0.0051,1.0000 5.000,0.7460,0.01954,0.01366,-0.0618,0.0047,1.0000 5.250,0.7698,0.02258,0.01707,-0.0602,0.0047,1.0000 5.500,0.7878,0.02692,0.02191,-0.0575,0.0052,1.0000 5.750,0.8125,0.03169,0.02718,-0.0539,0.0097,1.0000 6.000,0.8276,0.03545,0.03129,-0.0511,0.0097,1.0000 6.250,0.8410,0.03903,0.03518,-0.0484,0.0094,1.0000 6.500,0.8523,0.04276,0.03919,-0.0458,0.0090,1.0000 6.750,0.8617,0.04644,0.04313,-0.0433,0.0085,1.0000 7.000,0.8691,0.05016,0.04707,-0.0409,0.0082,1.0000 7.250,0.8741,0.05394,0.05106,-0.0387,0.0079,1.0000 7.500,0.8766,0.05774,0.05503,-0.0366,0.0076,1.0000 7.750,0.8765,0.06160,0.05906,-0.0345,0.0074,1.0000 8.000,0.8731,0.06556,0.06316,-0.0326,0.0072,1.0000 8.250,0.8670,0.06941,0.06713,-0.0308,0.0071,1.0000 8.500,0.8546,0.07307,0.07089,-0.0285,0.0071,1.0000 8.750,0.8388,0.07703,0.07493,-0.0268,0.0071,1.0000 9.000,0.8225,0.08179,0.07977,-0.0272,0.0072,1.0000