Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe10k-il-50000 Airfoil,goe10k-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,20.599 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-goe10k-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.5491,0.10529,0.09845,-0.0053,1.0000,0.1573 -8.000,-0.5542,0.10329,0.09655,-0.0065,1.0000,0.1639 -7.750,-0.5702,0.10272,0.09614,-0.0108,1.0000,0.1659 -7.500,-0.5532,0.09679,0.09018,-0.0068,1.0000,0.1778 -7.250,-0.5501,0.09296,0.08642,-0.0069,1.0000,0.1854 -7.000,-0.5566,0.09132,0.08487,-0.0113,1.0000,0.1949 -6.750,-0.5478,0.08685,0.08044,-0.0090,1.0000,0.2085 -6.500,-0.5435,0.08329,0.07693,-0.0088,1.0000,0.2230 -6.250,-0.5435,0.08062,0.07430,-0.0111,1.0000,0.2399 -6.000,-0.5338,0.07621,0.06997,-0.0062,1.0000,0.2642 -5.750,-0.5298,0.07290,0.06673,-0.0046,1.0000,0.2908 -5.500,-0.5248,0.06978,0.06367,-0.0016,1.0000,0.3242 -5.250,-0.5214,0.06668,0.06065,0.0027,1.0000,0.3667 -4.500,-0.3662,0.05049,0.04405,0.0275,1.0000,0.7976 -4.250,-0.3902,0.04951,0.04326,0.0316,1.0000,0.7756 -4.000,-0.4191,0.04844,0.04240,0.0351,1.0000,0.7357 -3.750,-0.3525,0.03868,0.03018,-0.0322,1.0000,0.1487 -3.500,-0.3219,0.03487,0.02560,-0.0322,1.0000,0.1215 -3.250,-0.2935,0.03184,0.02179,-0.0313,1.0000,0.1099 -3.000,-0.2680,0.02874,0.01835,-0.0304,1.0000,0.1059 -2.750,-0.2408,0.02628,0.01534,-0.0292,1.0000,0.1069 -2.500,-0.2133,0.02399,0.01259,-0.0281,1.0000,0.1132 -2.250,-0.1853,0.02194,0.01035,-0.0271,1.0000,0.1312 -2.000,-0.1547,0.01978,0.00807,-0.0263,1.0000,0.1806 -1.750,-0.1009,0.01462,0.00535,-0.0290,1.0000,1.0000 -1.500,-0.0780,0.01461,0.00464,-0.0278,1.0000,1.0000 -1.250,-0.0554,0.01461,0.00418,-0.0268,1.0000,1.0000 -1.000,-0.0329,0.01464,0.00383,-0.0258,1.0000,1.0000 -0.750,-0.0104,0.01468,0.00356,-0.0248,1.0000,1.0000 -0.500,0.0121,0.01473,0.00332,-0.0238,1.0000,1.0000 -0.250,0.0344,0.01480,0.00320,-0.0229,1.0000,1.0000 0.000,0.0568,0.01489,0.00314,-0.0220,1.0000,1.0000 0.250,0.0792,0.01499,0.00311,-0.0211,1.0000,1.0000 0.500,0.1015,0.01511,0.00316,-0.0203,1.0000,1.0000 0.750,0.1237,0.01524,0.00325,-0.0194,1.0000,1.0000 1.000,0.1459,0.01539,0.00340,-0.0186,1.0000,1.0000 1.250,0.1680,0.01555,0.00361,-0.0177,1.0000,1.0000 1.500,0.1899,0.01573,0.00387,-0.0169,1.0000,1.0000 1.750,0.2119,0.01593,0.00418,-0.0161,1.0000,1.0000 2.000,0.2336,0.01616,0.00459,-0.0152,1.0000,1.0000 2.250,0.2553,0.01640,0.00503,-0.0144,1.0000,1.0000 2.500,0.2768,0.01667,0.00554,-0.0136,1.0000,1.0000 2.750,0.2982,0.01697,0.00616,-0.0128,1.0000,1.0000 3.000,0.3193,0.01730,0.00683,-0.0119,1.0000,1.0000 3.250,0.3402,0.01767,0.00760,-0.0111,1.0000,1.0000 3.500,0.3611,0.01808,0.00849,-0.0103,1.0000,1.0000 3.750,0.3817,0.01853,0.00962,-0.0094,1.0000,1.0000 4.000,0.5878,0.02881,0.01711,-0.0311,0.0935,1.0000 4.250,0.6166,0.03159,0.02038,-0.0299,0.0899,1.0000 4.500,0.6440,0.03490,0.02424,-0.0284,0.0943,1.0000 4.750,0.6696,0.03821,0.02811,-0.0266,0.1007,1.0000 5.000,0.6927,0.04217,0.03266,-0.0248,0.1108,1.0000 5.250,0.7170,0.04623,0.03762,-0.0230,0.1349,1.0000 5.500,0.7587,0.05384,0.04708,-0.0289,0.2792,1.0000 5.750,0.6807,0.04889,0.04347,-0.0451,0.4409,1.0000 6.000,0.6367,0.05424,0.04864,-0.0491,0.4748,1.0000 7.000,0.7524,0.08577,0.07964,-0.0588,0.4549,1.0000 7.250,0.7505,0.08842,0.08221,-0.0543,0.4064,1.0000 7.500,0.7636,0.09206,0.08584,-0.0500,0.3610,1.0000 7.750,0.7878,0.09669,0.09051,-0.0449,0.3175,1.0000 8.000,0.7703,0.09926,0.09295,-0.0454,0.2996,1.0000 8.250,0.7875,0.10408,0.09781,-0.0421,0.2716,1.0000 8.500,0.7810,0.10746,0.10110,-0.0424,0.2560,1.0000 8.750,0.7782,0.11117,0.10475,-0.0426,0.2407,1.0000 9.000,0.7805,0.11530,0.10884,-0.0424,0.2262,1.0000 9.250,0.7872,0.11989,0.11341,-0.0417,0.2120,1.0000