Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe419-il-200000 Airfoil,goe419-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,79.8352 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe419-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.3698,0.09578,0.09237,-0.0232,1.0000,0.0249 -7.750,-0.3718,0.09398,0.09063,-0.0234,1.0000,0.0253 -7.500,-0.3743,0.09224,0.08896,-0.0240,1.0000,0.0256 -7.250,-0.3708,0.08995,0.08671,-0.0264,1.0000,0.0258 -7.000,-0.3653,0.08739,0.08419,-0.0285,1.0000,0.0260 -6.750,-0.3583,0.08476,0.08159,-0.0307,1.0000,0.0261 -6.500,-0.3517,0.08206,0.07891,-0.0319,1.0000,0.0262 -6.250,-0.3462,0.07940,0.07626,-0.0325,1.0000,0.0263 -6.000,-0.3415,0.07683,0.07369,-0.0327,1.0000,0.0263 -5.750,-0.3358,0.07416,0.07100,-0.0329,1.0000,0.0264 -5.500,-0.3282,0.07133,0.06815,-0.0332,1.0000,0.0264 -5.250,-0.3272,0.06574,0.06257,-0.0337,1.0000,0.0270 -5.000,-0.3257,0.06192,0.05878,-0.0324,1.0000,0.0277 -4.750,-0.3008,0.05770,0.05446,-0.0356,0.9969,0.0290 -4.500,-0.2655,0.05342,0.05008,-0.0412,0.9930,0.0309 -4.250,-0.2269,0.04909,0.04559,-0.0470,0.9883,0.0334 -4.000,-0.1684,0.04532,0.04139,-0.0549,0.9843,0.0389 -3.750,-0.1314,0.03950,0.03527,-0.0597,0.9802,0.0402 -3.500,-0.0930,0.03835,0.03380,-0.0624,0.9746,0.0521 -3.250,-0.0640,0.03281,0.02827,-0.0659,0.9714,0.0552 -3.000,-0.0231,0.03082,0.02568,-0.0683,0.9655,0.0660 -2.750,0.0090,0.02719,0.02207,-0.0708,0.9606,0.0706 -2.500,0.0551,0.02333,0.01761,-0.0734,0.9574,0.0612 -2.000,0.1336,0.01660,0.00954,-0.0753,0.9463,0.0468 -1.750,0.1712,0.01514,0.00769,-0.0765,0.9406,0.0517 -1.500,0.2089,0.01421,0.00664,-0.0783,0.9351,0.0654 -1.250,0.2498,0.01296,0.00541,-0.0809,0.9320,0.0759 -1.000,0.2839,0.01230,0.00474,-0.0821,0.9246,0.0887 -0.750,0.3242,0.01139,0.00399,-0.0845,0.9199,0.1257 -0.500,0.3842,0.00889,0.00370,-0.0917,0.9195,1.0000 -0.250,0.4213,0.00878,0.00342,-0.0934,0.9100,1.0000 0.000,0.4601,0.00867,0.00317,-0.0956,0.9008,1.0000 0.250,0.4976,0.00859,0.00299,-0.0974,0.8904,1.0000 0.500,0.5302,0.00859,0.00290,-0.0982,0.8777,1.0000 0.750,0.5586,0.00865,0.00289,-0.0981,0.8631,1.0000 1.000,0.5852,0.00873,0.00291,-0.0977,0.8477,1.0000 1.250,0.6110,0.00882,0.00296,-0.0970,0.8322,1.0000 1.500,0.6364,0.00891,0.00306,-0.0963,0.8164,1.0000 1.750,0.6616,0.00900,0.00313,-0.0955,0.8007,1.0000 2.000,0.6867,0.00909,0.00320,-0.0947,0.7849,1.0000 2.250,0.7079,0.00910,0.00316,-0.0928,0.7544,1.0000 2.500,0.7265,0.00910,0.00297,-0.0900,0.7017,1.0000 2.750,0.7459,0.00935,0.00295,-0.0877,0.6465,1.0000 3.000,0.7604,0.00990,0.00313,-0.0844,0.5550,1.0000 3.250,0.7627,0.01139,0.00341,-0.0794,0.3405,1.0000 3.500,0.7636,0.01411,0.00456,-0.0751,0.0400,1.0000 3.750,0.7853,0.01477,0.00538,-0.0736,0.0334,1.0000 4.000,0.8068,0.01544,0.00626,-0.0722,0.0321,1.0000 4.250,0.8267,0.01626,0.00724,-0.0705,0.0309,1.0000 4.500,0.8444,0.01727,0.00834,-0.0686,0.0264,1.0000 4.750,0.8610,0.01852,0.00965,-0.0663,0.0258,1.0000 5.000,0.8795,0.01989,0.01106,-0.0643,0.0266,1.0000 5.250,0.9016,0.02155,0.01284,-0.0627,0.0290,1.0000 5.500,0.9313,0.02430,0.01549,-0.0624,0.0337,1.0000 5.750,0.9667,0.02585,0.01720,-0.0619,0.0458,1.0000 6.000,1.0172,0.02755,0.01967,-0.0604,0.0861,1.0000 7.750,1.0599,0.04272,0.03696,-0.0436,0.0327,1.0000 8.000,1.0653,0.04195,0.03676,-0.0391,0.0292,1.0000 8.250,1.0651,0.04561,0.04074,-0.0361,0.0274,1.0000 8.500,1.0615,0.04949,0.04488,-0.0332,0.0262,1.0000 8.750,1.0546,0.05333,0.04894,-0.0303,0.0254,1.0000 9.000,1.0430,0.05704,0.05283,-0.0271,0.0248,1.0000 9.250,1.0259,0.06032,0.05627,-0.0235,0.0246,1.0000 9.500,1.0054,0.06385,0.05996,-0.0208,0.0245,1.0000 9.750,0.9821,0.06794,0.06422,-0.0193,0.0247,1.0000 10.000,0.9566,0.07285,0.06930,-0.0192,0.0251,1.0000 10.250,0.9301,0.07870,0.07531,-0.0207,0.0258,1.0000 10.500,0.9033,0.08556,0.08230,-0.0236,0.0266,1.0000