Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca66206-il-1000000-n5 Airfoil,naca66206-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,66.5304 Max Cl/Cd alpha,5.5 Url,http://airfoiltools.com/polar/csv?polar=xf-naca66206-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.5083,0.08313,0.08149,-0.0211,1.0000,0.0039 -7.750,-0.5108,0.07951,0.07790,-0.0236,1.0000,0.0039 -7.500,-0.5117,0.07533,0.07372,-0.0275,1.0000,0.0039 -7.250,-0.5081,0.07117,0.06953,-0.0302,1.0000,0.0039 -7.000,-0.5040,0.06695,0.06528,-0.0322,1.0000,0.0039 -6.750,-0.4987,0.06298,0.06127,-0.0333,1.0000,0.0039 -6.500,-0.4790,0.05756,0.05574,-0.0379,0.9928,0.0039 -6.250,-0.4562,0.05228,0.05033,-0.0420,0.9878,0.0039 -6.000,-0.4323,0.04711,0.04501,-0.0454,0.9823,0.0039 -5.750,-0.4066,0.04219,0.03990,-0.0483,0.9768,0.0039 -5.500,-0.3887,0.03462,0.03198,-0.0510,0.9673,0.0033 -5.250,-0.3657,0.02994,0.02700,-0.0515,0.9587,0.0028 -5.000,-0.3426,0.02558,0.02229,-0.0510,0.9506,0.0025 -4.750,-0.3199,0.02067,0.01692,-0.0496,0.9420,0.0021 -4.500,-0.2988,0.01164,0.00682,-0.0462,0.9338,0.0016 -4.250,-0.2744,0.00989,0.00475,-0.0453,0.9277,0.0015 -4.000,-0.2491,0.00896,0.00363,-0.0448,0.9215,0.0015 -3.750,-0.2233,0.00833,0.00284,-0.0444,0.9158,0.0015 -3.500,-0.1968,0.00788,0.00225,-0.0441,0.9104,0.0017 -3.250,-0.1699,0.00760,0.00186,-0.0439,0.9047,0.0021 -3.000,-0.1430,0.00739,0.00165,-0.0438,0.8996,0.0030 -2.750,-0.1158,0.00724,0.00141,-0.0438,0.8942,0.0029 -2.500,-0.0886,0.00711,0.00125,-0.0437,0.8894,0.0036 -2.250,-0.0614,0.00696,0.00112,-0.0438,0.8845,0.0080 -2.000,-0.0341,0.00692,0.00115,-0.0439,0.8793,0.0111 -1.750,-0.0069,0.00674,0.00091,-0.0438,0.8746,0.0168 -1.500,0.0207,0.00664,0.00083,-0.0438,0.8696,0.0204 -1.250,0.0481,0.00654,0.00075,-0.0438,0.8649,0.0294 -1.000,0.0753,0.00634,0.00067,-0.0439,0.8604,0.0776 -0.750,0.1008,0.00549,0.00057,-0.0441,0.8549,0.3373 -0.500,0.1225,0.00416,0.00054,-0.0436,0.8489,0.7538 -0.250,0.1481,0.00404,0.00059,-0.0431,0.8408,0.8111 0.000,0.1743,0.00402,0.00061,-0.0427,0.8315,0.8369 0.250,0.2007,0.00403,0.00062,-0.0423,0.8169,0.8502 0.500,0.2257,0.00414,0.00060,-0.0416,0.7757,0.8594 0.750,0.2506,0.00432,0.00059,-0.0410,0.7212,0.8657 1.000,0.2735,0.00477,0.00063,-0.0400,0.6064,0.8715 1.250,0.2922,0.00596,0.00090,-0.0388,0.3552,0.8773 1.500,0.3141,0.00683,0.00112,-0.0382,0.1662,0.8835 1.750,0.3386,0.00733,0.00130,-0.0378,0.0664,0.8893 2.000,0.3645,0.00757,0.00144,-0.0376,0.0340,0.8951 2.250,0.3912,0.00773,0.00163,-0.0374,0.0247,0.9009 2.500,0.4173,0.00790,0.00179,-0.0372,0.0179,0.9067 2.750,0.4433,0.00816,0.00210,-0.0368,0.0139,0.9133 3.000,0.4692,0.00830,0.00228,-0.0365,0.0136,0.9193 3.250,0.4954,0.00846,0.00247,-0.0363,0.0128,0.9258 3.500,0.5209,0.00862,0.00267,-0.0360,0.0112,0.9323 3.750,0.5464,0.00887,0.00294,-0.0355,0.0089,0.9398 4.000,0.5703,0.00927,0.00345,-0.0347,0.0080,0.9479 4.250,0.5940,0.00983,0.00413,-0.0339,0.0077,0.9573 4.500,0.6185,0.01052,0.00502,-0.0333,0.0072,0.9685 4.750,0.6432,0.01241,0.00714,-0.0329,0.0057,0.9845 5.000,0.6763,0.01133,0.00594,-0.0345,0.0051,1.0000 5.250,0.7055,0.01089,0.00538,-0.0352,0.0036,1.0000 5.500,0.7325,0.01101,0.00545,-0.0353,0.0024,1.0000 5.750,0.7571,0.01167,0.00619,-0.0349,0.0017,1.0000 6.000,0.7819,0.01228,0.00689,-0.0346,0.0015,1.0000 6.250,0.8065,0.01299,0.00771,-0.0342,0.0013,1.0000 6.500,0.8310,0.01369,0.00852,-0.0338,0.0010,1.0000 6.750,0.8562,0.01424,0.00919,-0.0336,0.0008,1.0000 7.000,0.8798,0.01534,0.01045,-0.0331,0.0006,1.0000 7.250,0.9013,0.01749,0.01295,-0.0321,0.0005,1.0000 7.500,0.8472,0.05103,0.04886,-0.0181,0.0006,1.0000 7.750,0.8474,0.05761,0.05568,-0.0168,0.0007,1.0000 8.000,0.8447,0.06385,0.06210,-0.0162,0.0007,1.0000 8.250,0.8403,0.06940,0.06777,-0.0162,0.0007,1.0000 8.500,0.8319,0.07480,0.07327,-0.0169,0.0007,1.0000 8.750,0.8199,0.07881,0.07734,-0.0170,0.0007,1.0000 9.000,0.8028,0.08390,0.08246,-0.0195,0.0008,1.0000