Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e428-il-50000 Airfoil,e428-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,22.0874 Max Cl/Cd alpha,4.5 Url,http://airfoiltools.com/polar/csv?polar=xf-e428-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.5210,0.10005,0.09223,0.0243,1.0000,0.4121 -8.250,-0.4946,0.09577,0.08786,0.0246,1.0000,0.4258 -8.000,-0.6198,0.07761,0.07009,0.0014,1.0000,0.2773 -7.750,-0.6201,0.07189,0.06435,-0.0013,1.0000,0.2725 -7.500,-0.6341,0.06471,0.05715,-0.0059,1.0000,0.2693 -7.250,-0.6493,0.05716,0.04946,-0.0107,1.0000,0.2690 -7.000,-0.6562,0.05050,0.04250,-0.0141,1.0000,0.2723 -6.750,-0.6514,0.04561,0.03728,-0.0156,1.0000,0.2786 -6.500,-0.6336,0.04349,0.03505,-0.0150,1.0000,0.2889 -6.250,-0.6174,0.04092,0.03231,-0.0147,1.0000,0.2988 -6.000,-0.6035,0.03781,0.02878,-0.0152,1.0000,0.3107 -5.750,-0.5813,0.03664,0.02765,-0.0139,1.0000,0.3227 -5.500,-0.5609,0.03517,0.02613,-0.0130,1.0000,0.3356 -5.250,-0.5410,0.03350,0.02431,-0.0123,1.0000,0.3490 -5.000,-0.5209,0.03171,0.02230,-0.0120,1.0000,0.3624 -4.750,-0.4988,0.03047,0.02101,-0.0111,1.0000,0.3748 -4.500,-0.4769,0.02926,0.01980,-0.0102,1.0000,0.3870 -4.250,-0.4550,0.02790,0.01830,-0.0096,1.0000,0.3995 -4.000,-0.4329,0.02670,0.01698,-0.0090,1.0000,0.4134 -3.750,-0.4107,0.02572,0.01594,-0.0082,1.0000,0.4280 -3.500,-0.3886,0.02486,0.01514,-0.0070,1.0000,0.4416 -3.250,-0.3667,0.02403,0.01435,-0.0060,1.0000,0.4567 -3.000,-0.3451,0.02327,0.01362,-0.0050,1.0000,0.4729 -2.750,-0.3240,0.02259,0.01298,-0.0038,1.0000,0.4904 -2.500,-0.3033,0.02196,0.01241,-0.0027,1.0000,0.5093 -2.250,-0.2828,0.02138,0.01187,-0.0016,1.0000,0.5304 -2.000,-0.2640,0.02089,0.01154,-0.0001,1.0000,0.5518 -1.750,-0.2464,0.02047,0.01125,0.0016,1.0000,0.5755 -1.500,-0.2294,0.02010,0.01101,0.0033,1.0000,0.6039 -1.250,-0.2131,0.01979,0.01086,0.0051,1.0000,0.6370 -1.000,-0.1988,0.01953,0.01081,0.0074,1.0000,0.6761 -0.750,-0.1867,0.01928,0.01083,0.0103,1.0000,0.7268 -0.500,-0.1781,0.01900,0.01087,0.0141,1.0000,0.7922 -0.250,-0.1553,0.01873,0.01098,0.0161,1.0000,0.8964 0.000,-0.0713,0.01866,0.01077,0.0021,1.0000,1.0000 0.250,-0.0368,0.01910,0.01098,-0.0029,0.9887,1.0000 0.500,0.0633,0.01978,0.01155,-0.0172,0.9528,1.0000 0.750,0.1596,0.01981,0.01161,-0.0292,0.9156,1.0000 1.000,0.2449,0.01938,0.01123,-0.0377,0.8757,1.0000 1.250,0.2912,0.01915,0.01094,-0.0390,0.8319,1.0000 1.500,0.3190,0.01911,0.01077,-0.0368,0.7875,1.0000 1.750,0.3375,0.01926,0.01074,-0.0332,0.7398,1.0000 2.000,0.3555,0.01948,0.01074,-0.0295,0.6900,1.0000 2.250,0.3743,0.01980,0.01078,-0.0262,0.6386,1.0000 2.500,0.3946,0.02024,0.01093,-0.0235,0.5900,1.0000 2.750,0.4165,0.02078,0.01117,-0.0214,0.5484,1.0000 3.000,0.4394,0.02140,0.01155,-0.0199,0.5139,1.0000 3.250,0.4631,0.02213,0.01215,-0.0187,0.4852,1.0000 3.500,0.4875,0.02286,0.01268,-0.0177,0.4621,1.0000 3.750,0.5121,0.02367,0.01335,-0.0168,0.4420,1.0000 4.000,0.5369,0.02459,0.01423,-0.0161,0.4247,1.0000 4.250,0.5619,0.02551,0.01507,-0.0154,0.4094,1.0000 4.500,0.5862,0.02654,0.01616,-0.0148,0.3945,1.0000 4.750,0.6102,0.02777,0.01753,-0.0144,0.3818,1.0000 5.000,0.6341,0.02904,0.01886,-0.0138,0.3704,1.0000 5.250,0.6594,0.03009,0.01980,-0.0131,0.3597,1.0000 5.500,0.6807,0.03178,0.02181,-0.0128,0.3489,1.0000 5.750,0.7033,0.03333,0.02346,-0.0122,0.3394,1.0000 6.000,0.7262,0.03476,0.02495,-0.0116,0.3292,1.0000 6.250,0.7442,0.03705,0.02755,-0.0113,0.3201,1.0000 6.500,0.7700,0.03815,0.02850,-0.0103,0.3105,1.0000 6.750,0.7809,0.04127,0.03214,-0.0102,0.3011,1.0000 7.000,0.8020,0.04301,0.03390,-0.0094,0.2917,1.0000 7.250,0.8118,0.04627,0.03751,-0.0092,0.2829,1.0000 7.500,0.8279,0.04880,0.04014,-0.0086,0.2750,1.0000 7.750,0.8212,0.05433,0.04611,-0.0096,0.2697,1.0000 8.000,0.8548,0.05471,0.04631,-0.0077,0.2607,1.0000 8.250,0.8312,0.06233,0.05435,-0.0099,0.2592,1.0000 8.500,0.8070,0.07018,0.06236,-0.0128,0.2596,1.0000 8.750,0.7928,0.07724,0.06950,-0.0156,0.2613,1.0000 9.000,0.6054,0.10834,0.10022,-0.0486,0.4276,1.0000