Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ag47ct02r-il-100000 Airfoil,ag47ct02r-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,41.8623 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-ag47ct02r-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6310,0.11881,0.11395,0.0305,1.0000,0.0628 -8.750,-0.6338,0.11641,0.11165,0.0251,1.0000,0.0636 -8.500,-0.6358,0.11363,0.10894,0.0192,1.0000,0.0639 -8.250,-0.6270,0.10720,0.10250,0.0215,1.0000,0.0651 -8.000,-0.6134,0.10268,0.09796,0.0250,1.0000,0.0678 -7.750,-0.6076,0.09907,0.09439,0.0238,1.0000,0.0703 -7.500,-0.6036,0.09545,0.09081,0.0211,1.0000,0.0730 -7.250,-0.5972,0.09138,0.08677,0.0119,1.0000,0.0762 -7.000,-0.5833,0.08643,0.08166,-0.0051,1.0000,0.0777 -6.750,-0.5776,0.08157,0.07698,0.0043,1.0000,0.0798 -6.500,-0.5000,0.06490,0.06041,-0.0126,1.0000,0.0912 -6.250,-0.4902,0.06050,0.05622,-0.0044,1.0000,0.0940 -6.000,-0.4795,0.05635,0.05207,-0.0052,1.0000,0.0991 -5.750,-0.4677,0.04985,0.04538,-0.0139,1.0000,0.1061 -5.500,-0.4554,0.04629,0.04190,-0.0117,1.0000,0.1110 -5.250,-0.4398,0.04107,0.03652,-0.0158,1.0000,0.1214 -5.000,-0.4235,0.03691,0.03225,-0.0174,1.0000,0.1352 -4.750,-0.4071,0.03327,0.02858,-0.0177,1.0000,0.1509 -4.500,-0.4133,0.04500,0.03969,-0.0199,1.0000,0.1647 -4.250,-0.3902,0.04190,0.03643,-0.0213,1.0000,0.1903 -4.000,-0.3684,0.03903,0.03351,-0.0214,1.0000,0.2180 -3.750,-0.3215,0.03238,0.02587,-0.0262,1.0000,0.1496 -3.500,-0.2734,0.02429,0.01599,-0.0258,1.0000,0.0607 -3.250,-0.2446,0.02165,0.01291,-0.0252,1.0000,0.0593 -3.000,-0.2155,0.02023,0.01099,-0.0245,1.0000,0.0640 -2.750,-0.1884,0.01790,0.00860,-0.0241,1.0000,0.0696 -2.500,-0.1608,0.01634,0.00693,-0.0233,1.0000,0.0793 -2.250,-0.1344,0.01493,0.00568,-0.0227,1.0000,0.1001 -2.000,-0.1086,0.01340,0.00447,-0.0220,1.0000,0.1565 -1.750,-0.0800,0.00958,0.00363,-0.0205,1.0000,1.0000 -1.500,-0.0533,0.00954,0.00323,-0.0201,1.0000,1.0000 -1.250,-0.0269,0.00951,0.00291,-0.0197,1.0000,1.0000 -1.000,-0.0006,0.00950,0.00269,-0.0194,1.0000,1.0000 -0.750,0.0257,0.00949,0.00253,-0.0190,1.0000,1.0000 -0.500,0.0518,0.00950,0.00241,-0.0187,1.0000,1.0000 -0.250,0.0778,0.00952,0.00232,-0.0184,1.0000,1.0000 0.000,0.1037,0.00955,0.00229,-0.0180,1.0000,1.0000 0.250,0.1294,0.00959,0.00230,-0.0177,1.0000,1.0000 0.500,0.1549,0.00966,0.00236,-0.0175,1.0000,1.0000 0.750,0.1800,0.00975,0.00246,-0.0173,1.0000,1.0000 1.000,0.2048,0.00988,0.00264,-0.0172,1.0000,1.0000 1.250,0.2287,0.01009,0.00291,-0.0172,1.0000,1.0000 1.500,0.2662,0.01037,0.00328,-0.0203,0.9882,1.0000 1.750,0.3284,0.01046,0.00350,-0.0271,0.9457,1.0000 2.000,0.3739,0.01050,0.00359,-0.0297,0.8916,1.0000 2.250,0.4034,0.01065,0.00367,-0.0286,0.8345,1.0000 2.500,0.4264,0.01092,0.00380,-0.0263,0.7804,1.0000 2.750,0.4486,0.01130,0.00404,-0.0240,0.7293,1.0000 3.000,0.4713,0.01170,0.00430,-0.0221,0.6757,1.0000 3.250,0.4943,0.01198,0.00446,-0.0204,0.6131,1.0000 3.500,0.5170,0.01235,0.00457,-0.0187,0.5336,1.0000 3.750,0.5394,0.01301,0.00478,-0.0172,0.4344,1.0000 4.000,0.5621,0.01401,0.00528,-0.0161,0.3352,1.0000 4.250,0.5856,0.01514,0.00595,-0.0155,0.2621,1.0000 4.500,0.6100,0.01627,0.00681,-0.0149,0.2146,1.0000 4.750,0.6345,0.01742,0.00771,-0.0144,0.1815,1.0000 5.000,0.6598,0.01856,0.00882,-0.0139,0.1565,1.0000 5.250,0.6853,0.01985,0.01014,-0.0133,0.1369,1.0000 5.500,0.7107,0.02109,0.01142,-0.0128,0.1196,1.0000 5.750,0.7365,0.02280,0.01325,-0.0122,0.1076,1.0000 6.000,0.7616,0.02431,0.01489,-0.0118,0.0948,1.0000 6.250,0.7863,0.02665,0.01732,-0.0113,0.0870,1.0000 6.500,0.8114,0.02885,0.02012,-0.0105,0.0800,1.0000 6.750,0.8339,0.03135,0.02288,-0.0101,0.0728,1.0000 7.000,0.8556,0.03511,0.02739,-0.0094,0.0700,1.0000 7.250,0.8739,0.03987,0.03287,-0.0089,0.0691,1.0000 7.500,0.8891,0.04485,0.03846,-0.0088,0.0677,1.0000 7.750,0.9062,0.04789,0.04124,-0.0088,0.0620,1.0000 8.000,0.9187,0.05287,0.04691,-0.0088,0.0633,1.0000 8.250,0.8518,0.08962,0.08509,-0.0403,0.1470,1.0000 8.500,0.8746,0.09161,0.08713,-0.0308,0.1408,1.0000