Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-lrn1007-il-200000-n5 Airfoil,lrn1007-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,98.7177 Max Cl/Cd alpha,5.75 Url,http://airfoiltools.com/polar/csv?polar=xf-lrn1007-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.1044,0.09039,0.08623,-0.0788,0.8373,0.0048 -8.250,-0.0971,0.08786,0.08373,-0.0799,0.8361,0.0056 -8.000,-0.0919,0.08819,0.08413,-0.0828,0.8340,0.0072 -7.750,-0.0858,0.08611,0.08208,-0.0839,0.8329,0.0072 -7.500,-0.0783,0.08460,0.08061,-0.0871,0.8316,0.0073 -7.250,-0.0663,0.08226,0.07827,-0.0901,0.8305,0.0073 -7.000,-0.0592,0.07696,0.07300,-0.0872,0.8301,0.0076 -6.750,-0.0484,0.07431,0.07035,-0.0891,0.8288,0.0077 -6.500,-0.0365,0.07167,0.06771,-0.0913,0.8276,0.0079 -6.250,-0.0223,0.06911,0.06512,-0.0940,0.8264,0.0079 -6.000,-0.0066,0.06649,0.06250,-0.0969,0.8247,0.0079 -5.750,0.0107,0.06381,0.05983,-0.1001,0.8228,0.0079 -5.500,0.0504,0.06266,0.05853,-0.1094,0.8208,0.0073 -5.250,0.0705,0.05981,0.05563,-0.1119,0.8195,0.0073 -5.000,0.0923,0.05700,0.05276,-0.1144,0.8183,0.0073 -4.750,0.1154,0.05427,0.04992,-0.1170,0.8171,0.0073 -4.500,0.1375,0.05147,0.04704,-0.1191,0.8158,0.0072 -4.250,0.1618,0.04882,0.04428,-0.1213,0.8146,0.0072 -4.000,0.1866,0.04622,0.04158,-0.1233,0.8136,0.0072 -3.750,0.2120,0.04369,0.03894,-0.1253,0.8127,0.0072 -3.500,0.2386,0.04141,0.03655,-0.1272,0.8112,0.0072 -3.250,0.2661,0.03930,0.03431,-0.1289,0.8095,0.0072 -3.000,0.2934,0.03725,0.03212,-0.1303,0.8077,0.0072 -2.750,0.3214,0.03537,0.03007,-0.1315,0.8059,0.0072 -2.500,0.3493,0.03356,0.02810,-0.1324,0.8045,0.0072 -2.250,0.3783,0.03203,0.02637,-0.1331,0.8032,0.0072 -2.000,0.4023,0.02942,0.02363,-0.1345,0.8019,0.0081 -1.750,0.4315,0.02834,0.02236,-0.1348,0.8008,0.0103 -1.500,0.4630,0.02831,0.02205,-0.1343,0.7996,0.0113 -1.250,0.4899,0.02755,0.02111,-0.1343,0.7965,0.0114 -1.000,0.5169,0.02585,0.01921,-0.1344,0.7933,0.0118 -0.750,0.5419,0.02330,0.01655,-0.1354,0.7908,0.0146 -0.500,0.5703,0.02252,0.01556,-0.1352,0.7890,0.0183 -0.250,0.6002,0.02237,0.01510,-0.1347,0.7875,0.0213 1.000,0.7346,0.01780,0.00998,-0.1340,0.7741,0.0493 1.250,0.7607,0.01751,0.00972,-0.1330,0.7699,0.0314 1.500,0.7864,0.01712,0.00930,-0.1323,0.7657,0.0214 1.750,0.8134,0.01634,0.00856,-0.1320,0.7628,0.0171 2.000,0.8419,0.01577,0.00790,-0.1318,0.7605,0.0143 2.250,0.8655,0.01570,0.00775,-0.1312,0.7544,0.0128 2.500,0.8927,0.01546,0.00736,-0.1309,0.7503,0.0125 2.750,0.9246,0.01362,0.00711,-0.1318,0.7478,1.0000 3.000,0.9484,0.01374,0.00715,-0.1312,0.7413,1.0000 3.250,0.9753,0.01360,0.00696,-0.1309,0.7363,1.0000 3.500,1.0009,0.01354,0.00692,-0.1305,0.7305,1.0000 3.750,1.0256,0.01351,0.00696,-0.1301,0.7236,1.0000 4.000,1.0496,0.01351,0.00705,-0.1295,0.7159,1.0000 4.250,1.0748,0.01338,0.00700,-0.1291,0.7081,1.0000 4.750,1.1184,0.01353,0.00731,-0.1275,0.6805,1.0000 5.000,1.1437,0.01328,0.00711,-0.1269,0.6646,1.0000 5.250,1.1729,0.01275,0.00655,-0.1268,0.6464,1.0000 5.500,1.2006,0.01239,0.00612,-0.1264,0.6197,1.0000 5.750,1.2241,0.01240,0.00594,-0.1253,0.5751,1.0000 6.000,1.2408,0.01293,0.00617,-0.1233,0.5211,1.0000 6.250,1.2367,0.01456,0.00703,-0.1181,0.4087,1.0000 6.500,1.2302,0.01625,0.00811,-0.1129,0.3164,1.0000 6.750,1.2170,0.01816,0.00933,-0.1068,0.2178,1.0000 7.000,1.2075,0.02031,0.01076,-0.1020,0.1179,1.0000 7.250,1.1954,0.02310,0.01273,-0.0972,0.0103,1.0000 7.500,1.2063,0.02431,0.01406,-0.0950,0.0061,1.0000 7.750,1.2170,0.02561,0.01564,-0.0927,0.0049,1.0000 8.000,1.2210,0.02753,0.01780,-0.0899,0.0023,1.0000 8.250,1.2266,0.02938,0.01990,-0.0873,0.0020,1.0000 8.500,1.2290,0.03153,0.02225,-0.0844,0.0019,1.0000 8.750,1.2318,0.03381,0.02468,-0.0817,0.0018,1.0000