Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca16006-il-1000000-n5 Airfoil,naca16006-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,36.163 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-naca16006-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.5161,0.08279,0.08125,-0.0118,1.0000,0.0059 -8.750,-0.5202,0.07815,0.07662,-0.0134,1.0000,0.0059 -8.500,-0.5257,0.07334,0.07183,-0.0155,1.0000,0.0059 -8.250,-0.5336,0.06836,0.06686,-0.0187,1.0000,0.0059 -8.000,-0.5470,0.06339,0.06188,-0.0227,1.0000,0.0059 -7.750,-0.5596,0.05949,0.05799,-0.0228,1.0000,0.0059 -7.500,-0.5664,0.05514,0.05359,-0.0227,1.0000,0.0059 -7.250,-0.5712,0.05091,0.04926,-0.0218,1.0000,0.0059 -7.000,-0.5744,0.04681,0.04508,-0.0203,1.0000,0.0059 -6.750,-0.5765,0.04291,0.04109,-0.0182,1.0000,0.0059 -6.500,-0.5774,0.03916,0.03725,-0.0156,1.0000,0.0059 -4.000,-0.4109,0.01489,0.01005,-0.0075,0.9866,0.0049 -3.750,-0.3843,0.01240,0.00725,-0.0065,0.9850,0.0040 -3.500,-0.3589,0.01041,0.00505,-0.0054,0.9832,0.0033 -3.250,-0.3326,0.00919,0.00365,-0.0049,0.9814,0.0029 -3.000,-0.3041,0.00853,0.00286,-0.0051,0.9800,0.0027 -2.750,-0.2746,0.00811,0.00234,-0.0055,0.9786,0.0025 -2.500,-0.2444,0.00784,0.00191,-0.0061,0.9775,0.0023 -2.250,-0.2160,0.00762,0.00163,-0.0063,0.9754,0.0022 -2.000,-0.1889,0.00746,0.00141,-0.0063,0.9723,0.0022 -1.750,-0.1601,0.00732,0.00126,-0.0066,0.9700,0.0024 -1.500,-0.1307,0.00721,0.00114,-0.0071,0.9679,0.0030 -1.250,-0.1009,0.00711,0.00108,-0.0077,0.9660,0.0044 -1.000,-0.0787,0.00641,0.00099,-0.0069,0.9613,0.1786 -0.750,-0.0704,0.00429,0.00077,-0.0036,0.9552,0.7261 -0.500,-0.0525,0.00377,0.00087,-0.0011,0.9505,0.8911 -0.250,-0.0273,0.00376,0.00094,-0.0002,0.9445,0.9245 0.000,0.0000,0.00376,0.00095,0.0000,0.9369,0.9369 0.250,0.0273,0.00376,0.00094,0.0002,0.9245,0.9445 0.500,0.0525,0.00377,0.00087,0.0011,0.8903,0.9505 0.750,0.0705,0.00428,0.00077,0.0036,0.7268,0.9552 1.000,0.0784,0.00646,0.00100,0.0069,0.1646,0.9614 1.250,0.1010,0.00711,0.00108,0.0077,0.0044,0.9661 1.500,0.1307,0.00721,0.00114,0.0071,0.0030,0.9679 1.750,0.1601,0.00732,0.00126,0.0066,0.0024,0.9700 2.000,0.1889,0.00746,0.00141,0.0063,0.0022,0.9724 2.250,0.2159,0.00762,0.00163,0.0064,0.0022,0.9755 2.500,0.2444,0.00784,0.00191,0.0061,0.0023,0.9775 2.750,0.2746,0.00812,0.00235,0.0055,0.0025,0.9787 3.000,0.3042,0.00853,0.00286,0.0051,0.0026,0.9800 3.250,0.3327,0.00920,0.00366,0.0049,0.0029,0.9815 3.500,0.3590,0.01041,0.00505,0.0054,0.0033,0.9832 3.750,0.3844,0.01241,0.00727,0.0065,0.0040,0.9851 4.000,0.4112,0.01489,0.01005,0.0074,0.0049,0.9867 8.000,0.6373,0.07715,0.07558,0.0154,0.0058,1.0000 8.250,0.6352,0.08161,0.08007,0.0132,0.0058,1.0000 8.500,0.6307,0.08655,0.08501,0.0083,0.0058,1.0000