Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca16006-il-200000-n5 Airfoil,naca16006-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,33.4335 Max Cl/Cd alpha,1.75 Url,http://airfoiltools.com/polar/csv?polar=xf-naca16006-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.5166,0.08591,0.08258,-0.0164,1.0000,0.0171 -8.750,-0.5210,0.08124,0.07793,-0.0186,1.0000,0.0172 -5.500,-0.5810,0.03940,0.03437,-0.0067,1.0000,0.0081 -5.250,-0.5705,0.03576,0.03042,-0.0041,1.0000,0.0077 -5.000,-0.5573,0.03237,0.02664,-0.0014,1.0000,0.0074 -4.750,-0.5420,0.02912,0.02301,0.0012,1.0000,0.0071 -4.500,-0.5242,0.02616,0.01963,0.0037,1.0000,0.0071 -4.250,-0.5031,0.02422,0.01732,0.0058,1.0000,0.0083 -4.000,-0.4819,0.02198,0.01463,0.0078,1.0000,0.0091 -3.750,-0.4593,0.01945,0.01169,0.0094,1.0000,0.0092 -3.500,-0.4357,0.01718,0.00911,0.0108,1.0000,0.0096 -3.250,-0.4130,0.01550,0.00725,0.0121,1.0000,0.0103 -3.000,-0.3909,0.01452,0.00616,0.0133,1.0000,0.0126 -2.750,-0.3687,0.01367,0.00518,0.0145,1.0000,0.0158 -2.500,-0.3463,0.01285,0.00425,0.0157,1.0000,0.0211 -2.250,-0.3233,0.01221,0.00357,0.0166,1.0000,0.0411 -2.000,-0.3022,0.01092,0.00309,0.0172,1.0000,0.2285 -1.750,-0.2892,0.00864,0.00282,0.0199,1.0000,0.7247 -1.500,-0.2420,0.00881,0.00340,0.0177,1.0000,0.9394 -1.250,-0.1173,0.00940,0.00364,-0.0022,1.0000,0.9909 -1.000,-0.0797,0.00935,0.00349,-0.0048,1.0000,0.9957 -0.750,-0.0433,0.00929,0.00336,-0.0071,1.0000,0.9995 -0.500,-0.0263,0.00925,0.00328,-0.0053,1.0000,1.0000 -0.250,-0.0130,0.00922,0.00324,-0.0027,1.0000,1.0000 0.000,0.0000,0.00921,0.00322,0.0000,1.0000,1.0000 0.250,0.0130,0.00922,0.00324,0.0027,1.0000,1.0000 0.500,0.0263,0.00925,0.00328,0.0053,1.0000,1.0000 0.750,0.0433,0.00929,0.00336,0.0071,0.9995,1.0000 1.000,0.0797,0.00936,0.00349,0.0048,0.9957,1.0000 1.250,0.1174,0.00940,0.00364,0.0022,0.9909,1.0000 1.500,0.2421,0.00881,0.00340,-0.0177,0.9391,1.0000 1.750,0.2892,0.00865,0.00282,-0.0198,0.7227,1.0000 2.000,0.3022,0.01093,0.00310,-0.0173,0.2277,1.0000 2.250,0.3234,0.01221,0.00357,-0.0166,0.0410,1.0000 2.500,0.3464,0.01286,0.00426,-0.0157,0.0211,1.0000 2.750,0.3688,0.01367,0.00518,-0.0146,0.0158,1.0000 3.000,0.3910,0.01453,0.00616,-0.0133,0.0126,1.0000 3.250,0.4131,0.01550,0.00726,-0.0121,0.0103,1.0000 3.500,0.4358,0.01718,0.00911,-0.0108,0.0096,1.0000 3.750,0.4595,0.01946,0.01171,-0.0094,0.0092,1.0000 4.000,0.4821,0.02200,0.01467,-0.0078,0.0091,1.0000 4.250,0.5034,0.02418,0.01728,-0.0058,0.0083,1.0000 4.500,0.5244,0.02617,0.01964,-0.0038,0.0071,1.0000 4.750,0.5421,0.02912,0.02301,-0.0013,0.0071,1.0000 5.000,0.5575,0.03238,0.02665,0.0014,0.0074,1.0000 5.250,0.5706,0.03577,0.03043,0.0041,0.0077,1.0000 5.500,0.5811,0.03940,0.03437,0.0067,0.0081,1.0000 7.500,0.6282,0.07266,0.06897,0.0191,0.0171,1.0000 9.500,0.6300,0.10746,0.10389,-0.0004,0.0166,1.0000 10.500,0.5050,0.11112,0.10769,0.0080,0.0170,1.0000 11.000,0.5039,0.11871,0.11526,0.0055,0.0169,1.0000