Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e850-il-100000-n5 Airfoil,e850-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,41.5346 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-e850-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.5036,0.09771,0.09261,-0.0310,1.0000,0.0137 -9.000,-0.5075,0.09323,0.08821,-0.0325,1.0000,0.0131 -8.500,-0.5177,0.08353,0.07866,-0.0364,1.0000,0.0119 -8.000,-0.4530,0.06609,0.06148,-0.0395,1.0000,0.0108 -7.750,-0.4675,0.06162,0.05705,-0.0404,1.0000,0.0107 -7.500,-0.4872,0.05820,0.05364,-0.0403,1.0000,0.0106 -7.250,-0.5524,0.06495,0.06002,-0.0410,1.0000,0.0108 -7.000,-0.5595,0.06104,0.05603,-0.0409,1.0000,0.0106 -6.750,-0.5629,0.05711,0.05196,-0.0406,1.0000,0.0104 -6.500,-0.5629,0.05300,0.04765,-0.0404,1.0000,0.0102 -6.250,-0.5584,0.04899,0.04339,-0.0402,1.0000,0.0100 -6.000,-0.5499,0.04509,0.03918,-0.0400,1.0000,0.0098 -5.750,-0.5378,0.04122,0.03494,-0.0397,1.0000,0.0096 -5.500,-0.5221,0.03753,0.03082,-0.0394,1.0000,0.0094 -5.250,-0.5035,0.03420,0.02703,-0.0390,1.0000,0.0092 -5.000,-0.4823,0.03114,0.02348,-0.0385,1.0000,0.0091 -4.750,-0.4594,0.02841,0.02028,-0.0380,1.0000,0.0089 -4.500,-0.4351,0.02597,0.01726,-0.0373,1.0000,0.0089 -4.250,-0.4105,0.02398,0.01494,-0.0366,1.0000,0.0089 -4.000,-0.3860,0.02223,0.01294,-0.0358,1.0000,0.0090 -3.750,-0.3617,0.02073,0.01124,-0.0350,1.0000,0.0093 -3.500,-0.3374,0.01951,0.00981,-0.0344,1.0000,0.0098 -3.250,-0.3124,0.01857,0.00859,-0.0340,1.0000,0.0106 -3.000,-0.2872,0.01769,0.00756,-0.0338,1.0000,0.0178 -2.750,-0.2605,0.01460,0.00669,-0.0355,1.0000,0.4351 -2.500,-0.2421,0.01446,0.00703,-0.0330,1.0000,0.6047 -2.250,-0.2214,0.01449,0.00701,-0.0312,1.0000,0.6494 -2.000,-0.2005,0.01451,0.00696,-0.0296,1.0000,0.6800 -1.750,-0.1779,0.01449,0.00670,-0.0287,1.0000,0.6957 -1.500,-0.1508,0.01452,0.00661,-0.0288,0.9984,0.7093 -1.250,-0.1201,0.01462,0.00661,-0.0296,0.9953,0.7232 -1.000,-0.0891,0.01472,0.00664,-0.0305,0.9923,0.7376 -0.750,-0.0593,0.01478,0.00666,-0.0312,0.9888,0.7526 -0.500,-0.0285,0.01489,0.00668,-0.0321,0.9852,0.7691 -0.250,0.0033,0.01502,0.00682,-0.0332,0.9819,0.7871 0.000,0.0321,0.01506,0.00689,-0.0336,0.9777,0.8079 0.250,0.0613,0.01509,0.00699,-0.0341,0.9732,0.8329 0.500,0.0937,0.01516,0.00716,-0.0352,0.9694,0.8664 0.750,0.1284,0.01510,0.00723,-0.0368,0.9648,0.9239 1.000,0.1666,0.01513,0.00729,-0.0396,0.9594,1.0000 1.250,0.2046,0.01536,0.00751,-0.0422,0.9554,1.0000 1.500,0.2347,0.01546,0.00765,-0.0432,0.9482,1.0000 1.750,0.2735,0.01564,0.00789,-0.0458,0.9434,1.0000 2.000,0.3045,0.01573,0.00806,-0.0467,0.9351,1.0000 2.250,0.3432,0.01581,0.00828,-0.0491,0.9282,1.0000 2.500,0.3809,0.01580,0.00863,-0.0511,0.9187,1.0000 2.750,0.4204,0.01562,0.00868,-0.0531,0.9061,1.0000 3.000,0.4657,0.01495,0.00830,-0.0554,0.8834,1.0000 3.250,0.5110,0.01375,0.00740,-0.0565,0.8402,1.0000 3.500,0.5819,0.01401,0.00601,-0.0611,0.3723,1.0000 3.750,0.5937,0.01643,0.00692,-0.0589,0.1009,1.0000 4.000,0.6129,0.01794,0.00811,-0.0573,0.0458,1.0000 4.250,0.6331,0.01929,0.00953,-0.0556,0.0304,1.0000 4.500,0.6534,0.02076,0.01111,-0.0540,0.0220,1.0000 4.750,0.6756,0.02222,0.01263,-0.0530,0.0168,1.0000 5.000,0.7007,0.02522,0.01575,-0.0521,0.0151,1.0000 5.250,0.7284,0.02750,0.01833,-0.0515,0.0145,1.0000 5.500,0.7546,0.03018,0.02141,-0.0505,0.0140,1.0000 5.750,0.7777,0.03321,0.02494,-0.0489,0.0137,1.0000 6.000,0.7970,0.03655,0.02879,-0.0469,0.0135,1.0000 6.250,0.8128,0.04010,0.03284,-0.0446,0.0134,1.0000 6.500,0.8251,0.04394,0.03715,-0.0420,0.0134,1.0000 6.750,0.8359,0.04768,0.04133,-0.0394,0.0130,1.0000 7.000,0.8444,0.05153,0.04558,-0.0369,0.0122,1.0000 7.250,0.8502,0.05550,0.04990,-0.0345,0.0113,1.0000 7.500,0.8528,0.05955,0.05425,-0.0323,0.0105,1.0000 7.750,0.8523,0.06363,0.05858,-0.0303,0.0099,1.0000 8.000,0.8490,0.06753,0.06267,-0.0286,0.0091,1.0000 8.250,0.8408,0.07191,0.06723,-0.0270,0.0096,1.0000 8.500,0.8283,0.07581,0.07124,-0.0253,0.0095,1.0000 8.750,0.8143,0.08012,0.07564,-0.0249,0.0097,1.0000 9.000,0.8001,0.08518,0.08076,-0.0262,0.0103,1.0000 9.250,0.7885,0.09090,0.08651,-0.0295,0.0106,1.0000