Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca66206-il-100000 Airfoil,naca66206-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,28.4364 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-naca66206-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.5432,0.09681,0.09191,-0.0216,1.0000,0.0593 -8.250,-0.5508,0.09359,0.08876,-0.0266,1.0000,0.0596 -8.000,-0.5546,0.09050,0.08562,-0.0313,1.0000,0.0599 -7.750,-0.5396,0.08423,0.07949,-0.0240,1.0000,0.0639 -7.500,-0.5369,0.08057,0.07585,-0.0256,1.0000,0.0665 -7.250,-0.5355,0.07674,0.07200,-0.0285,1.0000,0.0696 -7.000,-0.5344,0.07357,0.06868,-0.0336,1.0000,0.0725 -6.500,-0.5231,0.06508,0.06024,-0.0328,1.0000,0.0786 -6.250,-0.5165,0.06334,0.05804,-0.0356,1.0000,0.0863 -6.000,-0.5094,0.05783,0.05276,-0.0340,1.0000,0.0899 -5.750,-0.5002,0.05587,0.05035,-0.0348,1.0000,0.1006 -5.500,-0.4905,0.05147,0.04622,-0.0329,1.0000,0.1068 -5.250,-0.4804,0.04838,0.04300,-0.0322,1.0000,0.1189 -5.000,-0.4694,0.04558,0.04008,-0.0312,1.0000,0.1343 -4.750,-0.4588,0.04282,0.03719,-0.0303,1.0000,0.1568 -4.500,-0.4482,0.04020,0.03449,-0.0287,1.0000,0.1849 -4.250,-0.4388,0.03784,0.03219,-0.0266,1.0000,0.2250 -3.250,-0.3138,0.02514,0.01662,-0.0245,1.0000,0.0826 -3.000,-0.2863,0.02279,0.01376,-0.0228,1.0000,0.0689 -2.750,-0.2599,0.02087,0.01140,-0.0214,1.0000,0.0631 -2.500,-0.2348,0.01942,0.00972,-0.0202,1.0000,0.0618 -2.250,-0.2110,0.01800,0.00831,-0.0192,1.0000,0.0665 -2.000,-0.1875,0.01694,0.00720,-0.0182,1.0000,0.0750 -1.750,-0.1646,0.01585,0.00610,-0.0172,1.0000,0.0814 -1.500,-0.1414,0.01504,0.00523,-0.0163,1.0000,0.0949 -1.250,-0.1098,0.01166,0.00496,-0.0136,1.0000,1.0000 -1.000,-0.0925,0.01168,0.00465,-0.0121,1.0000,1.0000 -0.750,-0.0733,0.01174,0.00446,-0.0111,1.0000,1.0000 -0.500,-0.0529,0.01182,0.00436,-0.0103,1.0000,1.0000 -0.250,-0.0317,0.01193,0.00431,-0.0096,1.0000,1.0000 0.000,-0.0102,0.01206,0.00427,-0.0090,1.0000,1.0000 0.250,0.0117,0.01222,0.00432,-0.0085,1.0000,1.0000 0.500,0.0337,0.01240,0.00442,-0.0080,1.0000,1.0000 0.750,0.0557,0.01259,0.00456,-0.0076,1.0000,1.0000 1.000,0.0778,0.01281,0.00475,-0.0072,1.0000,1.0000 1.250,0.0999,0.01305,0.00499,-0.0068,1.0000,1.0000 1.500,0.1219,0.01332,0.00528,-0.0065,1.0000,1.0000 1.750,0.1438,0.01360,0.00559,-0.0061,1.0000,1.0000 2.000,0.1655,0.01392,0.00596,-0.0058,1.0000,1.0000 2.250,0.1871,0.01426,0.00637,-0.0054,1.0000,1.0000 2.500,0.2084,0.01463,0.00684,-0.0051,1.0000,1.0000 2.750,0.2296,0.01504,0.00737,-0.0048,1.0000,1.0000 3.000,0.2673,0.01570,0.00835,-0.0079,0.9934,1.0000 3.250,0.4692,0.01650,0.00642,-0.0274,0.0806,1.0000 3.500,0.4899,0.01778,0.00766,-0.0260,0.0677,1.0000 3.750,0.5128,0.01982,0.00951,-0.0249,0.0634,1.0000 4.000,0.5410,0.02158,0.01150,-0.0241,0.0622,1.0000 4.250,0.5704,0.02399,0.01408,-0.0235,0.0627,1.0000 4.500,0.5979,0.02584,0.01634,-0.0225,0.0603,1.0000 4.750,0.6246,0.02837,0.01927,-0.0214,0.0602,1.0000 5.000,0.6534,0.03168,0.02321,-0.0196,0.0728,1.0000 6.750,0.7864,0.05953,0.05421,-0.0111,0.1189,1.0000 7.000,0.8005,0.06584,0.06027,-0.0108,0.1031,1.0000 7.250,0.7959,0.06698,0.06208,-0.0102,0.0935,1.0000 7.500,0.8061,0.07309,0.06805,-0.0099,0.0891,1.0000 7.750,0.7954,0.07553,0.07093,-0.0109,0.0829,1.0000 8.000,0.8055,0.07960,0.07497,-0.0101,0.0784,1.0000 8.250,0.8107,0.08607,0.08136,-0.0102,0.0761,1.0000 8.500,0.7937,0.08916,0.08466,-0.0122,0.0753,1.0000 8.750,0.7766,0.09300,0.08855,-0.0146,0.0745,1.0000 9.000,0.7663,0.09790,0.09344,-0.0189,0.0741,1.0000 9.250,0.7576,0.10317,0.09865,-0.0243,0.0725,1.0000 9.500,0.7542,0.10791,0.10334,-0.0276,0.0699,1.0000 9.750,0.7553,0.11225,0.10767,-0.0294,0.0676,1.0000 10.000,0.6609,0.11367,0.10942,-0.0240,0.0755,1.0000 10.250,0.6499,0.11825,0.11396,-0.0280,0.0743,1.0000