Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe05k-il-50000 Airfoil,goe05k-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,20.5159 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe05k-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.5621,0.10889,0.10220,-0.0093,1.0000,0.1390 -8.000,-0.5477,0.10313,0.09640,-0.0073,1.0000,0.1507 -7.750,-0.5586,0.10200,0.09541,-0.0103,1.0000,0.1537 -7.500,-0.5483,0.09712,0.09055,-0.0081,1.0000,0.1658 -7.250,-0.5454,0.09347,0.08697,-0.0084,1.0000,0.1748 -7.000,-0.5497,0.09175,0.08534,-0.0129,1.0000,0.1833 -6.750,-0.5449,0.08800,0.08165,-0.0125,1.0000,0.1980 -6.500,-0.5415,0.08479,0.07848,-0.0134,1.0000,0.2133 -6.250,-0.5335,0.08027,0.07403,-0.0100,1.0000,0.2324 -6.000,-0.5310,0.07754,0.07134,-0.0107,1.0000,0.2573 -5.750,-0.5252,0.07392,0.06778,-0.0076,1.0000,0.2859 -5.500,-0.5222,0.07068,0.06460,-0.0054,1.0000,0.3197 -5.250,-0.5184,0.06746,0.06147,-0.0001,1.0000,0.3650 -5.000,-0.2326,0.04542,0.03841,0.0007,1.0000,0.9683 -4.750,-0.2491,0.04484,0.03803,0.0060,1.0000,0.9441 -4.500,-0.2852,0.04541,0.03878,0.0146,1.0000,0.9013 -4.250,-0.3236,0.04582,0.03941,0.0224,1.0000,0.8565 -4.000,-0.3602,0.04570,0.03953,0.0286,1.0000,0.8129 -3.750,-0.3947,0.04528,0.03934,0.0342,1.0000,0.7795 -3.500,-0.4314,0.04423,0.03856,0.0396,1.0000,0.7429 -3.250,-0.3004,0.03497,0.02633,-0.0344,1.0000,0.1804 -3.000,-0.2647,0.03200,0.02248,-0.0345,1.0000,0.1367 -2.750,-0.2345,0.02919,0.01906,-0.0336,1.0000,0.1155 -2.500,-0.2056,0.02690,0.01623,-0.0325,1.0000,0.1025 -2.250,-0.1766,0.02508,0.01379,-0.0311,1.0000,0.0946 -2.000,-0.1486,0.02321,0.01153,-0.0299,1.0000,0.0956 -1.750,-0.1203,0.02123,0.00932,-0.0287,1.0000,0.0992 -1.500,-0.0917,0.01962,0.00753,-0.0278,1.0000,0.1145 -1.250,-0.0651,0.01808,0.00599,-0.0270,1.0000,0.1540 -1.000,-0.0213,0.01448,0.00427,-0.0282,1.0000,1.0000 -0.750,0.0018,0.01451,0.00364,-0.0271,1.0000,1.0000 -0.500,0.0246,0.01456,0.00328,-0.0262,1.0000,1.0000 -0.250,0.0472,0.01463,0.00303,-0.0254,1.0000,1.0000 0.000,0.0698,0.01472,0.00288,-0.0245,1.0000,1.0000 0.250,0.0923,0.01482,0.00278,-0.0237,1.0000,1.0000 0.500,0.1147,0.01494,0.00279,-0.0230,1.0000,1.0000 0.750,0.1371,0.01508,0.00285,-0.0222,1.0000,1.0000 1.000,0.1592,0.01523,0.00300,-0.0214,1.0000,1.0000 1.250,0.1814,0.01540,0.00322,-0.0207,1.0000,1.0000 1.500,0.2033,0.01559,0.00350,-0.0199,1.0000,1.0000 1.750,0.2252,0.01580,0.00385,-0.0191,1.0000,1.0000 2.000,0.2469,0.01604,0.00429,-0.0183,1.0000,1.0000 2.250,0.2685,0.01630,0.00489,-0.0175,1.0000,1.0000 2.500,0.2900,0.01658,0.00549,-0.0168,1.0000,1.0000 2.750,0.3114,0.01691,0.00623,-0.0160,1.0000,1.0000 3.000,0.3325,0.01727,0.00721,-0.0150,1.0000,1.0000 3.250,0.3540,0.01766,0.00840,-0.0140,1.0000,1.0000 3.500,0.5369,0.02617,0.01402,-0.0332,0.0821,1.0000 3.750,0.5702,0.02878,0.01699,-0.0324,0.0809,1.0000 4.000,0.6008,0.03231,0.02075,-0.0317,0.0844,1.0000 4.250,0.6307,0.03462,0.02387,-0.0297,0.0955,1.0000 4.500,0.6591,0.03793,0.02782,-0.0280,0.1108,1.0000 4.750,0.6884,0.04129,0.03204,-0.0263,0.1376,1.0000 5.000,0.7224,0.04542,0.03727,-0.0257,0.1956,1.0000 5.250,0.7744,0.05366,0.04764,-0.0446,0.4131,1.0000 5.500,0.7559,0.06147,0.05574,-0.0633,0.5182,1.0000 5.750,0.7201,0.06643,0.06052,-0.0698,0.5761,1.0000 6.000,0.6762,0.06936,0.06317,-0.0717,0.6257,1.0000 7.000,0.7255,0.08528,0.07905,-0.0667,0.5181,1.0000 7.250,0.7525,0.08956,0.08336,-0.0615,0.4523,1.0000 7.500,0.7675,0.09309,0.08691,-0.0560,0.3915,1.0000 7.750,0.7787,0.09668,0.09049,-0.0520,0.3467,1.0000 8.000,0.7944,0.10103,0.09482,-0.0476,0.3037,1.0000 8.250,0.7828,0.10387,0.09757,-0.0479,0.2837,1.0000 8.500,0.7943,0.10847,0.10215,-0.0455,0.2585,1.0000