Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe627-il-50000 Airfoil,goe627-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,25.4001 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-goe627-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.3236,0.11169,0.10532,-0.0146,1.0000,0.3311 -8.500,-0.3121,0.10816,0.10184,-0.0128,1.0000,0.3401 -8.250,-0.3574,0.10905,0.10293,-0.0098,1.0000,0.3513 -8.000,-0.3184,0.10390,0.09773,-0.0086,1.0000,0.3620 -7.750,-0.3362,0.10231,0.09627,-0.0059,1.0000,0.3732 -7.500,-0.3572,0.10166,0.09575,-0.0025,1.0000,0.3874 -7.250,-0.3381,0.09774,0.09186,-0.0013,1.0000,0.3946 -7.000,-0.3630,0.09673,0.09099,0.0025,1.0000,0.4088 -6.750,-0.3511,0.09389,0.08819,0.0043,1.0000,0.4186 -6.500,-0.3597,0.09195,0.08635,0.0074,1.0000,0.4315 -5.750,-0.5944,0.06218,0.05545,-0.0095,1.0000,0.1720 -5.500,-0.5890,0.05868,0.05181,-0.0079,1.0000,0.1666 -5.250,-0.5886,0.05400,0.04632,-0.0063,1.0000,0.1555 -5.000,-0.5793,0.05124,0.04334,-0.0045,1.0000,0.1527 -4.750,-0.5697,0.04857,0.04032,-0.0027,1.0000,0.1500 -4.500,-0.5585,0.04639,0.03777,-0.0009,1.0000,0.1495 -4.250,-0.5460,0.04457,0.03561,0.0008,1.0000,0.1500 -4.000,-0.5322,0.04293,0.03363,0.0025,1.0000,0.1507 -3.750,-0.5173,0.04145,0.03183,0.0041,1.0000,0.1511 -3.500,-0.5014,0.04017,0.03026,0.0056,1.0000,0.1519 -3.250,-0.4849,0.03912,0.02892,0.0069,1.0000,0.1535 -3.000,-0.4684,0.03837,0.02787,0.0082,1.0000,0.1563 -2.750,-0.4325,0.03792,0.02741,0.0060,0.9932,0.1629 -2.500,-0.3721,0.03796,0.02718,0.0001,0.9739,0.1735 -2.250,-0.3116,0.03785,0.02721,-0.0058,0.9561,0.1928 -2.000,-0.0503,0.03701,0.02999,-0.0401,0.9469,1.0000 -1.750,-0.0069,0.03730,0.02984,-0.0445,0.9271,1.0000 -1.500,0.0386,0.03758,0.02976,-0.0488,0.9083,1.0000 -1.250,0.0755,0.03771,0.02960,-0.0514,0.8887,1.0000 -1.000,0.1077,0.03777,0.02941,-0.0528,0.8682,1.0000 -0.750,0.1451,0.03779,0.02921,-0.0548,0.8488,1.0000 -0.500,0.1858,0.03769,0.02889,-0.0570,0.8299,1.0000 -0.250,0.2278,0.03748,0.02847,-0.0592,0.8116,1.0000 0.000,0.2716,0.03710,0.02791,-0.0613,0.7937,1.0000 0.250,0.3154,0.03659,0.02724,-0.0631,0.7761,1.0000 0.500,0.3605,0.03590,0.02640,-0.0649,0.7589,1.0000 0.750,0.4068,0.03505,0.02542,-0.0666,0.7423,1.0000 1.000,0.4588,0.03406,0.02429,-0.0692,0.7258,1.0000 1.250,0.5135,0.03301,0.02312,-0.0722,0.7089,1.0000 1.500,0.5658,0.03195,0.02192,-0.0747,0.6915,1.0000 1.750,0.6142,0.03109,0.02093,-0.0768,0.6735,1.0000 2.000,0.6581,0.03048,0.02017,-0.0783,0.6550,1.0000 2.250,0.6960,0.03017,0.01970,-0.0790,0.6363,1.0000 2.500,0.7234,0.03030,0.01970,-0.0783,0.6186,1.0000 2.750,0.7450,0.03065,0.01993,-0.0769,0.6016,1.0000 3.000,0.7610,0.03124,0.02044,-0.0746,0.5857,1.0000 3.250,0.7756,0.03194,0.02106,-0.0723,0.5712,1.0000 3.500,0.7972,0.03251,0.02154,-0.0710,0.5583,1.0000 3.750,0.8316,0.03274,0.02160,-0.0716,0.5460,1.0000 4.000,0.8231,0.03425,0.02319,-0.0661,0.5343,1.0000 4.250,0.8410,0.03505,0.02392,-0.0644,0.5240,1.0000 4.500,0.8547,0.03599,0.02483,-0.0622,0.5140,1.0000 4.750,0.8550,0.03752,0.02637,-0.0582,0.5055,1.0000 5.000,0.8646,0.03876,0.02762,-0.0556,0.4973,1.0000 5.250,0.8722,0.04020,0.02905,-0.0528,0.4901,1.0000 5.500,0.8370,0.04326,0.03221,-0.0448,0.4832,1.0000 5.750,0.9066,0.04238,0.03116,-0.0498,0.4754,1.0000 6.000,0.7844,0.04941,0.03841,-0.0324,0.4709,1.0000 6.250,0.5739,0.06879,0.05783,-0.0218,0.4661,1.0000 6.500,0.5490,0.07441,0.06344,-0.0212,0.4651,1.0000 6.750,0.5323,0.07925,0.06828,-0.0209,0.4649,1.0000 7.000,0.5155,0.08411,0.07314,-0.0208,0.4668,1.0000 7.250,0.5092,0.08848,0.07751,-0.0212,0.4713,1.0000 7.500,0.5264,0.09178,0.08082,-0.0219,0.4751,1.0000