Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe444-il-1000000-n5 Airfoil,goe444-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,34.0629 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe444-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.6344,0.08204,0.08052,-0.0029,1.0000,0.0039 -8.000,-0.6432,0.07711,0.07562,-0.0076,1.0000,0.0039 -7.750,-0.6471,0.07202,0.07050,-0.0109,1.0000,0.0035 -7.500,-0.6461,0.06730,0.06573,-0.0134,1.0000,0.0038 -7.250,-0.6429,0.06271,0.06106,-0.0150,1.0000,0.0041 -7.000,-0.6381,0.05815,0.05640,-0.0159,1.0000,0.0041 -6.750,-0.6313,0.05371,0.05179,-0.0160,1.0000,0.0043 -6.500,-0.6225,0.04950,0.04744,-0.0156,1.0000,0.0045 -6.250,-0.6121,0.04547,0.04325,-0.0147,1.0000,0.0048 -6.000,-0.6001,0.04161,0.03921,-0.0134,1.0000,0.0050 -5.750,-0.5860,0.03801,0.03539,-0.0117,1.0000,0.0054 -5.500,-0.5655,0.03515,0.03232,-0.0095,1.0000,0.0061 -5.250,-0.5480,0.03251,0.02945,-0.0075,1.0000,0.0062 -5.000,-0.5315,0.02977,0.02647,-0.0053,1.0000,0.0062 -4.750,-0.5149,0.02718,0.02362,-0.0030,1.0000,0.0063 -4.500,-0.4979,0.02478,0.02092,-0.0007,1.0000,0.0063 -2.750,-0.3126,0.00946,0.00400,0.0024,0.9891,0.0049 -2.500,-0.2821,0.00821,0.00260,0.0021,0.9862,0.0036 -2.250,-0.2530,0.00762,0.00189,0.0019,0.9807,0.0030 -2.000,-0.2197,0.00727,0.00146,0.0008,0.9770,0.0026 -1.750,-0.1895,0.00705,0.00118,0.0002,0.9697,0.0025 -1.500,-0.1557,0.00688,0.00096,-0.0012,0.9633,0.0024 -1.250,-0.1207,0.00675,0.00081,-0.0029,0.9536,0.0025 -1.000,-0.0852,0.00664,0.00069,-0.0047,0.9389,0.0034 -0.750,-0.0611,0.00519,0.00051,-0.0047,0.9117,0.3985 -0.500,-0.0371,0.00476,0.00041,-0.0041,0.8792,0.5275 -0.250,-0.0169,0.00436,0.00038,-0.0025,0.8466,0.6706 0.000,0.0001,0.00418,0.00038,0.0000,0.7839,0.7825 0.250,0.0177,0.00431,0.00038,0.0024,0.6849,0.8459 0.500,0.0375,0.00472,0.00041,0.0040,0.5384,0.8790 0.750,0.0613,0.00517,0.00050,0.0047,0.4050,0.9112 1.000,0.0852,0.00664,0.00069,0.0047,0.0034,0.9390 1.250,0.1208,0.00675,0.00081,0.0028,0.0026,0.9538 1.500,0.1556,0.00688,0.00096,0.0012,0.0024,0.9633 1.750,0.1896,0.00705,0.00117,-0.0003,0.0024,0.9698 2.000,0.2194,0.00727,0.00146,-0.0007,0.0026,0.9767 2.250,0.2525,0.00761,0.00188,-0.0019,0.0030,0.9805 2.500,0.2817,0.00827,0.00267,-0.0020,0.0037,0.9860 2.750,0.3120,0.00947,0.00401,-0.0023,0.0050,0.9890 3.000,0.3415,0.01070,0.00545,-0.0024,0.0054,0.9916 3.250,0.3677,0.01517,0.01014,-0.0011,0.0106,0.9936 3.500,0.3970,0.01718,0.01238,-0.0011,0.0106,0.9955 3.750,0.4273,0.01892,0.01441,-0.0013,0.0105,0.9974 4.000,0.4610,0.01881,0.01450,-0.0014,0.0085,0.9988 4.250,0.4884,0.02038,0.01627,-0.0016,0.0072,1.0000 4.500,0.4984,0.02482,0.02097,0.0007,0.0063,1.0000 4.750,0.5153,0.02719,0.02363,0.0029,0.0063,1.0000 5.000,0.5318,0.02979,0.02650,0.0052,0.0062,1.0000 5.250,0.5483,0.03251,0.02946,0.0074,0.0062,1.0000 5.500,0.5653,0.03523,0.03240,0.0095,0.0061,1.0000 5.750,0.5855,0.03800,0.03539,0.0116,0.0056,1.0000 6.000,0.6001,0.04161,0.03920,0.0134,0.0050,1.0000 6.250,0.6121,0.04548,0.04326,0.0148,0.0046,1.0000 6.500,0.6223,0.04945,0.04740,0.0157,0.0046,1.0000 6.750,0.6310,0.05368,0.05177,0.0161,0.0044,1.0000 7.000,0.6378,0.05806,0.05627,0.0160,0.0041,1.0000 7.250,0.6427,0.06259,0.06094,0.0151,0.0041,1.0000 7.500,0.6452,0.06742,0.06584,0.0135,0.0039,1.0000 7.750,0.6464,0.07208,0.07056,0.0110,0.0037,1.0000 8.000,0.6427,0.07707,0.07558,0.0077,0.0040,1.0000 8.250,0.6342,0.08192,0.08041,0.0030,0.0041,1.0000