Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe118-il-500000-n5 Airfoil,goe118-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,108.943 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-goe118-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.2245,0.09991,0.09755,-0.0487,0.8845,0.0061 -8.500,-0.2179,0.09701,0.09456,-0.0500,0.8623,0.0062 -8.250,-0.2109,0.09407,0.09154,-0.0515,0.8430,0.0062 -8.000,-0.2035,0.09101,0.08842,-0.0532,0.8253,0.0063 -7.750,-0.1958,0.08787,0.08522,-0.0550,0.8096,0.0063 -7.500,-0.1876,0.08468,0.08195,-0.0569,0.7953,0.0063 -7.250,-0.1793,0.08152,0.07874,-0.0591,0.7825,0.0063 -7.000,-0.1724,0.07689,0.07408,-0.0627,0.7718,0.0065 -6.500,-0.1443,0.06984,0.06693,-0.0700,0.7524,0.0068 -6.250,-0.1267,0.06631,0.06335,-0.0743,0.7439,0.0069 -6.000,-0.1064,0.06260,0.05958,-0.0792,0.7356,0.0071 -5.750,-0.0834,0.05864,0.05556,-0.0847,0.7282,0.0073 -4.750,0.0400,0.03872,0.03515,-0.1107,0.7022,0.0056 -4.500,0.0747,0.03298,0.02917,-0.1164,0.6961,0.0050 -4.250,0.1142,0.02301,0.01858,-0.1222,0.6916,0.0043 -4.000,0.1471,0.01769,0.01242,-0.1242,0.6864,0.0040 -3.750,0.1762,0.01560,0.00986,-0.1248,0.6802,0.0041 -3.500,0.2049,0.01424,0.00813,-0.1251,0.6743,0.0044 -3.250,0.2336,0.01314,0.00674,-0.1253,0.6678,0.0049 -3.000,0.2619,0.01274,0.00612,-0.1253,0.6618,0.0061 -2.750,0.2905,0.01164,0.00482,-0.1255,0.6555,0.0066 -2.500,0.3187,0.01080,0.00381,-0.1256,0.6492,0.0071 -2.250,0.3471,0.01032,0.00325,-0.1258,0.6430,0.0081 -2.000,0.3753,0.01003,0.00285,-0.1259,0.6362,0.0099 -1.750,0.4037,0.00972,0.00238,-0.1260,0.6295,0.0129 -1.500,0.4318,0.00950,0.00203,-0.1261,0.6212,0.0186 -1.250,0.4598,0.00920,0.00180,-0.1263,0.6124,0.0710 -1.000,0.4875,0.00923,0.00178,-0.1264,0.6042,0.0898 -0.750,0.5154,0.00923,0.00175,-0.1266,0.5967,0.0987 -0.500,0.5431,0.00925,0.00171,-0.1267,0.5903,0.1037 -0.250,0.5711,0.00923,0.00164,-0.1269,0.5838,0.1052 0.000,0.5987,0.00925,0.00158,-0.1269,0.5765,0.1067 0.250,0.6264,0.00924,0.00155,-0.1271,0.5663,0.1106 0.500,0.6539,0.00926,0.00154,-0.1272,0.5568,0.1154 1.000,0.7090,0.00932,0.00158,-0.1274,0.5404,0.1324 1.250,0.7364,0.00934,0.00162,-0.1275,0.5326,0.1512 1.500,0.7639,0.00924,0.00170,-0.1278,0.5239,0.2278 1.750,0.7905,0.00860,0.00194,-0.1282,0.5154,0.6005 2.250,0.8409,0.00803,0.00208,-0.1272,0.4983,1.0000 2.500,0.8679,0.00818,0.00220,-0.1273,0.4908,1.0000 2.750,0.8949,0.00832,0.00232,-0.1273,0.4794,1.0000 3.250,0.9478,0.00870,0.00261,-0.1272,0.4496,1.0000 3.500,0.9714,0.00916,0.00287,-0.1267,0.4051,1.0000 3.750,0.9911,0.01006,0.00334,-0.1257,0.3258,1.0000 4.000,0.9997,0.01224,0.00456,-0.1232,0.1394,1.0000 4.250,1.0165,0.01349,0.00544,-0.1217,0.0219,1.0000 4.500,1.0405,0.01391,0.00592,-0.1211,0.0129,1.0000 4.750,1.0630,0.01450,0.00661,-0.1203,0.0084,1.0000 5.000,1.0855,0.01504,0.00725,-0.1195,0.0073,1.0000 5.250,1.1080,0.01552,0.00774,-0.1188,0.0057,1.0000 5.500,1.1264,0.01641,0.00874,-0.1174,0.0049,1.0000 5.750,1.1439,0.01731,0.00978,-0.1158,0.0044,1.0000 6.000,1.1585,0.01839,0.01098,-0.1137,0.0041,1.0000 6.250,1.1699,0.01962,0.01232,-0.1111,0.0039,1.0000 6.500,1.1786,0.02095,0.01376,-0.1082,0.0037,1.0000 6.750,1.1871,0.02204,0.01492,-0.1052,0.0035,1.0000 7.000,1.1940,0.02325,0.01617,-0.1024,0.0031,1.0000 7.250,1.2014,0.02462,0.01767,-0.0994,0.0027,1.0000 7.500,1.2074,0.02647,0.01962,-0.0962,0.0025,1.0000 7.750,1.2219,0.02845,0.02168,-0.0938,0.0023,1.0000 8.000,1.2552,0.03092,0.02423,-0.0937,0.0021,1.0000 8.250,1.3017,0.03450,0.02802,-0.0958,0.0022,1.0000 8.500,1.3316,0.03796,0.03171,-0.0954,0.0023,1.0000 8.750,1.3519,0.04121,0.03521,-0.0939,0.0025,1.0000 9.000,1.3660,0.04441,0.03865,-0.0919,0.0026,1.0000 9.250,1.3738,0.04767,0.04214,-0.0896,0.0028,1.0000 13.750,1.1464,0.12680,0.12451,-0.0723,0.0039,1.0000 14.000,1.1293,0.13473,0.13255,-0.0771,0.0039,1.0000 14.250,1.1134,0.14330,0.14122,-0.0826,0.0040,1.0000