Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca66206-il-50000-n5 Airfoil,naca66206-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,22.5504 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-naca66206-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.5480,0.11102,0.10394,-0.0105,1.0000,0.0851 -9.000,-0.5556,0.10869,0.10174,-0.0147,1.0000,0.0882 -8.750,-0.5665,0.10617,0.09935,-0.0197,1.0000,0.0890 -8.500,-0.5444,0.09999,0.09313,-0.0150,1.0000,0.0945 -8.250,-0.5443,0.09672,0.08993,-0.0167,1.0000,0.0982 -8.000,-0.5600,0.09428,0.08762,-0.0235,1.0000,0.1020 -7.750,-0.5501,0.08945,0.08285,-0.0217,1.0000,0.1057 -7.500,-0.5461,0.08581,0.07923,-0.0226,1.0000,0.1107 -7.250,-0.5505,0.08225,0.07570,-0.0266,1.0000,0.1179 -6.250,-0.5047,0.06362,0.05618,-0.0354,1.0000,0.0483 -6.000,-0.4950,0.05914,0.05174,-0.0348,1.0000,0.0470 -5.750,-0.4837,0.05540,0.04781,-0.0347,1.0000,0.0467 -5.500,-0.4708,0.05177,0.04393,-0.0343,1.0000,0.0465 -5.250,-0.4566,0.04819,0.04010,-0.0338,1.0000,0.0456 -5.000,-0.4408,0.04469,0.03630,-0.0331,1.0000,0.0439 -4.750,-0.4229,0.04135,0.03259,-0.0324,1.0000,0.0420 -4.500,-0.4031,0.03813,0.02891,-0.0314,1.0000,0.0405 -4.250,-0.3819,0.03519,0.02547,-0.0303,1.0000,0.0396 -4.000,-0.3596,0.03248,0.02228,-0.0292,1.0000,0.0395 -3.750,-0.3365,0.03006,0.01942,-0.0280,1.0000,0.0400 -3.500,-0.3132,0.02812,0.01705,-0.0269,1.0000,0.0447 -3.250,-0.2891,0.02624,0.01460,-0.0257,1.0000,0.0502 -3.000,-0.2654,0.02439,0.01258,-0.0243,1.0000,0.0524 -2.750,-0.2419,0.02293,0.01090,-0.0227,1.0000,0.0556 -2.500,-0.2189,0.02178,0.00946,-0.0212,1.0000,0.0595 -2.250,-0.1973,0.02070,0.00821,-0.0200,1.0000,0.0670 -2.000,-0.1756,0.01981,0.00721,-0.0190,1.0000,0.0885 -1.500,-0.1085,0.01550,0.00587,-0.0182,1.0000,1.0000 -1.250,-0.0933,0.01547,0.00539,-0.0162,1.0000,1.0000 -1.000,-0.0764,0.01548,0.00508,-0.0147,1.0000,1.0000 -0.750,-0.0581,0.01551,0.00485,-0.0134,1.0000,1.0000 -0.500,-0.0388,0.01557,0.00469,-0.0124,1.0000,1.0000 -0.250,-0.0188,0.01565,0.00459,-0.0114,1.0000,1.0000 0.000,0.0017,0.01576,0.00454,-0.0106,1.0000,1.0000 0.250,0.0226,0.01589,0.00450,-0.0099,1.0000,1.0000 0.500,0.0438,0.01605,0.00455,-0.0093,1.0000,1.0000 0.750,0.0652,0.01622,0.00466,-0.0087,1.0000,1.0000 1.000,0.0867,0.01642,0.00483,-0.0081,1.0000,1.0000 1.250,0.1082,0.01665,0.00505,-0.0076,1.0000,1.0000 1.500,0.1298,0.01689,0.00533,-0.0072,1.0000,1.0000 1.750,0.1513,0.01716,0.00565,-0.0067,1.0000,1.0000 2.000,0.1728,0.01746,0.00602,-0.0063,1.0000,1.0000 2.250,0.1942,0.01778,0.00645,-0.0059,1.0000,1.0000 2.500,0.2310,0.01830,0.00718,-0.0086,0.9915,1.0000 2.750,0.2689,0.01885,0.00809,-0.0115,0.9824,1.0000 3.000,0.3075,0.01938,0.00897,-0.0144,0.9722,1.0000 3.250,0.3474,0.01991,0.00994,-0.0174,0.9601,1.0000 3.500,0.4695,0.02082,0.00800,-0.0234,0.0932,1.0000 3.750,0.4912,0.02215,0.00941,-0.0223,0.0740,1.0000 4.000,0.5133,0.02364,0.01101,-0.0212,0.0658,1.0000 4.250,0.5400,0.02514,0.01285,-0.0202,0.0606,1.0000 4.500,0.5691,0.02707,0.01489,-0.0199,0.0514,1.0000 4.750,0.5988,0.02898,0.01712,-0.0194,0.0444,1.0000 5.000,0.6277,0.03159,0.02001,-0.0189,0.0421,1.0000 5.250,0.6539,0.03485,0.02360,-0.0183,0.0406,1.0000 5.500,0.6774,0.03869,0.02799,-0.0173,0.0400,1.0000 5.750,0.6990,0.04150,0.03149,-0.0158,0.0389,1.0000 6.000,0.7182,0.04440,0.03511,-0.0141,0.0357,1.0000 6.250,0.7344,0.04788,0.03913,-0.0127,0.0337,1.0000 6.500,0.7483,0.05182,0.04353,-0.0115,0.0340,1.0000 6.750,0.7596,0.05595,0.04808,-0.0104,0.0346,1.0000 7.000,0.7685,0.06021,0.05269,-0.0095,0.0353,1.0000 7.250,0.7751,0.06454,0.05730,-0.0088,0.0362,1.0000 7.500,0.7793,0.06901,0.06199,-0.0085,0.0372,1.0000 7.750,0.7819,0.07357,0.06670,-0.0083,0.0382,1.0000 8.000,0.7850,0.07784,0.07123,-0.0084,0.0423,1.0000 8.250,0.7774,0.08283,0.07640,-0.0099,0.0451,1.0000 8.500,0.7700,0.08753,0.08116,-0.0111,0.0474,1.0000 8.750,0.7650,0.09213,0.08576,-0.0124,0.0497,1.0000 9.000,0.6560,0.08801,0.08203,-0.0100,0.0439,1.0000 9.250,0.6464,0.09407,0.08806,-0.0137,0.0456,1.0000