Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ag11-il-50000 Airfoil,ag11-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,33.0181 Max Cl/Cd alpha,4.25 Url,http://airfoiltools.com/polar/csv?polar=xf-ag11-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.750,-0.5272,0.10598,0.09946,0.0114,1.0000,0.1518 -7.500,-0.5205,0.10187,0.09538,0.0108,1.0000,0.1570 -7.250,-0.5173,0.09911,0.09268,0.0079,1.0000,0.1662 -7.000,-0.5070,0.09484,0.08846,0.0086,1.0000,0.1748 -6.750,-0.5046,0.09186,0.08555,0.0026,1.0000,0.1836 -6.500,-0.4980,0.08924,0.08293,-0.0030,1.0000,0.1965 -6.250,-0.4875,0.08504,0.07881,-0.0023,1.0000,0.2112 -6.000,-0.4759,0.08080,0.07464,0.0005,1.0000,0.2276 -5.750,-0.4647,0.07728,0.07117,0.0017,1.0000,0.2475 -5.500,-0.4556,0.07388,0.06782,0.0006,1.0000,0.2712 -5.250,-0.4458,0.07060,0.06460,0.0015,1.0000,0.2997 -5.000,-0.4357,0.06744,0.06153,0.0046,1.0000,0.3333 -4.750,-0.4277,0.06449,0.05864,0.0085,1.0000,0.3767 -4.500,-0.1443,0.04397,0.03753,0.0139,1.0000,1.0000 -4.250,-0.1308,0.04149,0.03510,0.0123,1.0000,1.0000 -4.000,-0.1316,0.04007,0.03377,0.0141,1.0000,0.9938 -3.750,-0.1820,0.04177,0.03567,0.0268,1.0000,0.9484 -3.500,-0.2291,0.04274,0.03686,0.0361,1.0000,0.8909 -3.250,-0.2743,0.04306,0.03741,0.0424,1.0000,0.8304 -3.000,-0.1864,0.03539,0.02718,-0.0354,1.0000,0.1769 -2.750,-0.1477,0.03249,0.02342,-0.0363,1.0000,0.1373 -2.500,-0.1160,0.03028,0.02054,-0.0360,1.0000,0.1245 -2.250,-0.0890,0.02779,0.01789,-0.0355,1.0000,0.1209 -2.000,-0.0604,0.02577,0.01550,-0.0348,1.0000,0.1153 -1.750,-0.0317,0.02426,0.01352,-0.0337,1.0000,0.1116 -1.500,-0.0051,0.02257,0.01172,-0.0328,1.0000,0.1137 -1.250,0.0208,0.02134,0.01034,-0.0316,1.0000,0.1237 -1.000,0.0483,0.01999,0.00896,-0.0306,1.0000,0.1357 -0.750,0.0747,0.01876,0.00779,-0.0298,1.0000,0.1675 -0.500,0.1011,0.01463,0.00627,-0.0277,1.0000,1.0000 -0.250,0.1251,0.01477,0.00573,-0.0267,1.0000,1.0000 0.000,0.1480,0.01494,0.00557,-0.0260,1.0000,1.0000 0.250,0.1705,0.01516,0.00553,-0.0255,1.0000,1.0000 0.500,0.1928,0.01543,0.00563,-0.0251,1.0000,1.0000 0.750,0.2147,0.01578,0.00584,-0.0249,1.0000,1.0000 1.000,0.2360,0.01620,0.00616,-0.0248,1.0000,1.0000 1.250,0.2566,0.01673,0.00661,-0.0249,1.0000,1.0000 1.500,0.2764,0.01739,0.00722,-0.0252,1.0000,1.0000 1.750,0.2952,0.01820,0.00802,-0.0259,1.0000,1.0000 2.000,0.3511,0.01913,0.00898,-0.0335,0.9798,1.0000 2.250,0.4393,0.01955,0.00955,-0.0454,0.9357,1.0000 2.500,0.5130,0.01943,0.00965,-0.0527,0.8904,1.0000 2.750,0.5590,0.01924,0.00955,-0.0535,0.8441,1.0000 3.000,0.5875,0.01922,0.00952,-0.0510,0.7967,1.0000 3.250,0.6099,0.01934,0.00957,-0.0474,0.7485,1.0000 3.500,0.6308,0.01955,0.00964,-0.0437,0.7009,1.0000 3.750,0.6514,0.01995,0.00995,-0.0406,0.6501,1.0000 4.000,0.6729,0.02042,0.01020,-0.0377,0.6012,1.0000 4.250,0.6947,0.02104,0.01065,-0.0353,0.5504,1.0000 4.500,0.7170,0.02175,0.01111,-0.0332,0.5028,1.0000 4.750,0.7395,0.02259,0.01174,-0.0314,0.4560,1.0000 5.000,0.7623,0.02356,0.01262,-0.0298,0.4113,1.0000 5.250,0.7853,0.02465,0.01352,-0.0285,0.3709,1.0000 5.500,0.8087,0.02588,0.01464,-0.0273,0.3340,1.0000 5.750,0.8320,0.02721,0.01584,-0.0263,0.3013,1.0000 6.000,0.8562,0.02879,0.01740,-0.0254,0.2750,1.0000 6.250,0.8794,0.03044,0.01923,-0.0246,0.2503,1.0000 6.500,0.9031,0.03229,0.02113,-0.0239,0.2315,1.0000 6.750,0.9266,0.03462,0.02370,-0.0233,0.2175,1.0000 7.000,0.9487,0.03685,0.02622,-0.0226,0.2034,1.0000 7.250,0.9709,0.03908,0.02856,-0.0220,0.1912,1.0000 7.500,0.9874,0.04302,0.03334,-0.0216,0.1846,1.0000 7.750,1.0091,0.04587,0.03625,-0.0209,0.1780,1.0000 8.000,1.0166,0.05084,0.04207,-0.0208,0.1727,1.0000 8.250,1.0388,0.05303,0.04413,-0.0199,0.1638,1.0000 8.500,1.0415,0.05897,0.05075,-0.0202,0.1632,1.0000 8.750,1.0425,0.06516,0.05739,-0.0207,0.1635,1.0000 9.000,0.9952,0.07776,0.07062,-0.0273,0.1732,1.0000 9.250,0.9778,0.08634,0.07932,-0.0318,0.1795,1.0000