Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe711-il-50000 Airfoil,goe711-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,20.2779 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-goe711-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.500,-0.3516,0.12398,0.11854,-0.0173,1.0000,0.1725 -7.250,-0.3806,0.12400,0.11871,-0.0151,1.0000,0.1743 -7.000,-0.4109,0.12393,0.11877,-0.0145,1.0000,0.1752 -6.750,-0.3854,0.11859,0.11344,-0.0105,1.0000,0.1835 -6.500,-0.4032,0.11741,0.11237,-0.0088,1.0000,0.1883 -6.250,-0.4294,0.11672,0.11178,-0.0107,1.0000,0.1917 -6.000,-0.4239,0.11307,0.10821,-0.0069,1.0000,0.1977 -5.750,-0.4323,0.11127,0.10647,-0.0064,1.0000,0.2060 -5.500,-0.4446,0.10888,0.10414,-0.0084,1.0000,0.2115 -5.250,-0.4420,0.10649,0.10182,-0.0048,1.0000,0.2214 -5.000,-0.4482,0.10384,0.09922,-0.0061,1.0000,0.2298 -4.750,-0.4516,0.10203,0.09738,-0.0103,1.0000,0.2440 -4.500,-0.4486,0.09913,0.09459,-0.0037,1.0000,0.2519 -4.250,-0.4488,0.09663,0.09213,-0.0041,1.0000,0.2658 -4.000,-0.4161,0.09290,0.08836,-0.0097,0.9885,0.2984 -3.750,-0.3849,0.08978,0.08522,-0.0117,0.9748,0.3397 -3.250,0.0684,0.07308,0.06797,-0.0326,0.9840,1.0000 -3.000,0.1133,0.06943,0.06427,-0.0424,0.9666,1.0000 -2.750,0.1325,0.06711,0.06195,-0.0460,0.9489,0.9939 -2.500,0.0720,0.06774,0.06273,-0.0322,0.9284,0.9450 -2.250,0.0106,0.06798,0.06311,-0.0204,0.9112,0.8933 -2.000,-0.0479,0.06777,0.06305,-0.0099,0.8931,0.8572 -1.750,0.0359,0.05857,0.05106,-0.0887,0.8639,0.2480 -1.500,0.1029,0.05590,0.04745,-0.0955,0.8524,0.2051 -1.250,0.1475,0.05426,0.04522,-0.0983,0.8385,0.1885 -1.000,0.1909,0.05318,0.04344,-0.1004,0.8245,0.1752 -0.750,0.2292,0.05176,0.04182,-0.1021,0.8108,0.1707 -0.500,0.2673,0.05081,0.04057,-0.1035,0.7972,0.1694 -0.250,0.3064,0.04994,0.03940,-0.1048,0.7841,0.1712 0.000,0.3632,0.04817,0.03732,-0.1078,0.7754,0.1723 0.250,0.3945,0.04780,0.03674,-0.1077,0.7612,0.1745 0.500,0.4250,0.04734,0.03624,-0.1076,0.7473,0.1808 0.750,0.4559,0.04703,0.03583,-0.1076,0.7339,0.1921 1.000,0.5146,0.04479,0.03365,-0.1108,0.7274,0.2169 1.250,0.5455,0.04386,0.03348,-0.1114,0.7144,0.3249 1.500,0.5612,0.04288,0.03368,-0.1077,0.7009,1.0000 1.750,0.6260,0.04097,0.03099,-0.1109,0.6958,1.0000 2.000,0.6482,0.04159,0.03135,-0.1099,0.6822,1.0000 2.250,0.6644,0.04264,0.03221,-0.1084,0.6684,1.0000 2.500,0.6825,0.04365,0.03305,-0.1072,0.6555,1.0000 2.750,0.7507,0.04152,0.03060,-0.1115,0.6503,1.0000 3.000,0.7538,0.04348,0.03249,-0.1087,0.6364,1.0000 3.250,0.7573,0.04556,0.03449,-0.1060,0.6237,1.0000 3.500,0.8266,0.04333,0.03202,-0.1104,0.6186,1.0000 3.750,0.8073,0.04697,0.03568,-0.1054,0.6048,1.0000 4.000,0.8902,0.04390,0.03235,-0.1113,0.6013,1.0000 4.250,0.8495,0.04907,0.03762,-0.1042,0.5872,1.0000 4.500,0.7965,0.05651,0.04516,-0.0981,0.5728,1.0000 4.750,0.8279,0.05679,0.04534,-0.0983,0.5669,1.0000 5.250,0.7381,0.07294,0.06167,-0.0927,0.5461,1.0000 5.500,0.7492,0.07547,0.06417,-0.0924,0.5402,1.0000 5.750,0.7689,0.07740,0.06605,-0.0923,0.5358,1.0000 6.000,0.7254,0.08551,0.07425,-0.0910,0.5328,1.0000 6.250,0.7106,0.09071,0.07949,-0.0905,0.5310,1.0000 6.500,0.7032,0.09547,0.08428,-0.0905,0.5317,1.0000 6.750,0.7076,0.09968,0.08849,-0.0912,0.5348,1.0000 7.000,0.7232,0.10319,0.09200,-0.0922,0.5369,1.0000 7.250,0.5875,0.11866,0.10792,-0.0938,0.6418,1.0000 7.500,0.6086,0.12151,0.11072,-0.0947,0.6352,1.0000