Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe598-il-1000000-n5 Airfoil,goe598-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,60.8408 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-goe598-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6584,0.08946,0.08798,0.0085,1.0000,0.0018 -8.750,-0.6635,0.08356,0.08210,0.0045,1.0000,0.0018 -7.750,-0.7246,0.02034,0.01678,-0.0272,1.0000,0.0019 -7.500,-0.7035,0.01791,0.01392,-0.0266,1.0000,0.0020 -7.250,-0.6804,0.01630,0.01202,-0.0262,1.0000,0.0021 -7.000,-0.6561,0.01512,0.01062,-0.0258,1.0000,0.0022 -6.750,-0.6318,0.01395,0.00924,-0.0254,1.0000,0.0022 -6.500,-0.6079,0.01265,0.00773,-0.0250,1.0000,0.0025 -6.250,-0.5823,0.01215,0.00717,-0.0248,1.0000,0.0027 -6.000,-0.5568,0.01164,0.00659,-0.0245,1.0000,0.0030 -5.750,-0.5316,0.01098,0.00582,-0.0241,1.0000,0.0033 -5.500,-0.5064,0.01038,0.00512,-0.0236,1.0000,0.0036 -5.250,-0.4812,0.00993,0.00456,-0.0232,1.0000,0.0038 -5.000,-0.4509,0.00929,0.00382,-0.0239,0.9975,0.0045 -4.750,-0.4195,0.00891,0.00340,-0.0248,0.9945,0.0053 -4.500,-0.3887,0.00860,0.00304,-0.0256,0.9903,0.0062 -4.250,-0.3573,0.00822,0.00265,-0.0265,0.9859,0.0088 -4.000,-0.3264,0.00795,0.00236,-0.0273,0.9797,0.0129 -3.750,-0.2958,0.00776,0.00219,-0.0280,0.9722,0.0191 -3.500,-0.2660,0.00756,0.00197,-0.0285,0.9633,0.0236 -3.250,-0.2376,0.00742,0.00180,-0.0286,0.9522,0.0277 -3.000,-0.2103,0.00733,0.00165,-0.0284,0.9384,0.0296 -2.750,-0.1838,0.00721,0.00148,-0.0281,0.9203,0.0318 -2.500,-0.1578,0.00713,0.00131,-0.0276,0.8969,0.0335 -2.250,-0.1318,0.00709,0.00115,-0.0271,0.8698,0.0352 -2.000,-0.1054,0.00707,0.00103,-0.0267,0.8420,0.0371 -1.750,-0.0785,0.00702,0.00092,-0.0265,0.8177,0.0470 -1.500,-0.0513,0.00695,0.00086,-0.0264,0.7968,0.0728 -1.250,-0.0237,0.00695,0.00079,-0.0264,0.7781,0.0763 -1.000,0.0039,0.00693,0.00074,-0.0263,0.7607,0.0822 -0.750,0.0316,0.00692,0.00069,-0.0263,0.7426,0.0866 -0.500,0.0591,0.00696,0.00065,-0.0263,0.7158,0.0911 -0.250,0.0866,0.00697,0.00061,-0.0263,0.6867,0.1032 0.000,0.1138,0.00671,0.00057,-0.0264,0.6646,0.2045 0.250,0.1413,0.00658,0.00056,-0.0265,0.6429,0.2646 0.500,0.1683,0.00618,0.00054,-0.0267,0.6239,0.4095 0.750,0.1953,0.00597,0.00057,-0.0267,0.5989,0.5123 1.000,0.2223,0.00577,0.00062,-0.0268,0.5732,0.6092 1.250,0.2480,0.00545,0.00068,-0.0265,0.5420,0.7462 1.500,0.2709,0.00547,0.00078,-0.0255,0.4515,0.8565 1.750,0.2914,0.00573,0.00094,-0.0238,0.3548,0.9466 2.000,0.3247,0.00614,0.00109,-0.0253,0.2740,0.9867 2.250,0.3550,0.00675,0.00127,-0.0263,0.1592,1.0000 2.500,0.3817,0.00707,0.00143,-0.0263,0.1146,1.0000 2.750,0.4078,0.00754,0.00164,-0.0262,0.0491,1.0000 3.000,0.4344,0.00790,0.00187,-0.0261,0.0167,1.0000 3.250,0.4616,0.00812,0.00209,-0.0260,0.0108,1.0000 3.500,0.4887,0.00841,0.00244,-0.0258,0.0078,1.0000 3.750,0.5158,0.00863,0.00267,-0.0257,0.0065,1.0000 4.000,0.5427,0.00892,0.00298,-0.0256,0.0055,1.0000 4.250,0.5690,0.00941,0.00354,-0.0253,0.0046,1.0000 4.500,0.5956,0.00980,0.00399,-0.0251,0.0042,1.0000 4.750,0.6217,0.01032,0.00459,-0.0248,0.0038,1.0000 5.000,0.6478,0.01076,0.00508,-0.0246,0.0034,1.0000 5.250,0.6740,0.01114,0.00548,-0.0244,0.0031,1.0000 5.500,0.6982,0.01210,0.00655,-0.0239,0.0027,1.0000 5.750,0.7236,0.01276,0.00730,-0.0235,0.0026,1.0000 6.000,0.7484,0.01357,0.00823,-0.0230,0.0025,1.0000 6.250,0.7726,0.01464,0.00946,-0.0224,0.0023,1.0000 6.500,0.7964,0.01597,0.01101,-0.0216,0.0020,1.0000 6.750,0.8191,0.01772,0.01302,-0.0207,0.0018,1.0000 7.000,0.8402,0.02021,0.01586,-0.0196,0.0017,1.0000 7.250,0.8521,0.02677,0.02316,-0.0167,0.0017,1.0000 7.500,0.8517,0.03772,0.03494,-0.0126,0.0019,1.0000 7.750,0.8558,0.04476,0.04238,-0.0108,0.0020,1.0000 8.000,0.8581,0.05126,0.04917,-0.0098,0.0021,1.0000 8.250,0.8578,0.05741,0.05555,-0.0096,0.0021,1.0000 8.500,0.8538,0.06344,0.06175,-0.0102,0.0022,1.0000 8.750,0.8460,0.06953,0.06798,-0.0120,0.0022,1.0000 9.000,0.8311,0.07538,0.07392,-0.0147,0.0023,1.0000 9.250,0.8172,0.08457,0.08316,-0.0252,0.0023,1.0000