Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ag47c03-il-100000-n5 Airfoil,ag47c03-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,39.3282 Max Cl/Cd alpha,4.5 Url,http://airfoiltools.com/polar/csv?polar=xf-ag47c03-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.000,-0.5070,0.08799,0.08352,0.0159,1.0000,0.0425 -6.750,-0.5071,0.08380,0.07936,0.0144,1.0000,0.0426 -6.500,-0.5077,0.07953,0.07514,0.0125,1.0000,0.0424 -6.000,-0.5868,0.08185,0.07725,0.0109,1.0000,0.0411 -5.500,-0.5522,0.06809,0.06329,-0.0030,1.0000,0.0243 -5.250,-0.5367,0.06313,0.05825,-0.0064,1.0000,0.0231 -5.000,-0.5176,0.05769,0.05268,-0.0105,1.0000,0.0220 -4.750,-0.4959,0.05200,0.04678,-0.0144,1.0000,0.0210 -4.500,-0.4722,0.04649,0.04097,-0.0175,1.0000,0.0206 -4.250,-0.4475,0.04170,0.03585,-0.0198,1.0000,0.0215 -4.000,-0.4214,0.03716,0.03086,-0.0214,1.0000,0.0227 -3.750,-0.3948,0.03296,0.02616,-0.0223,1.0000,0.0233 -3.500,-0.3678,0.02915,0.02181,-0.0228,1.0000,0.0231 -3.250,-0.3402,0.02590,0.01795,-0.0228,1.0000,0.0233 -3.000,-0.3122,0.02321,0.01474,-0.0226,1.0000,0.0238 -2.750,-0.2842,0.02103,0.01212,-0.0222,1.0000,0.0246 -2.500,-0.2567,0.01921,0.00999,-0.0218,1.0000,0.0263 -2.250,-0.2303,0.01788,0.00863,-0.0216,1.0000,0.0311 -2.000,-0.2032,0.01658,0.00718,-0.0211,1.0000,0.0349 -1.750,-0.1766,0.01540,0.00593,-0.0207,1.0000,0.0413 -1.500,-0.1498,0.01449,0.00499,-0.0203,1.0000,0.0532 -1.250,-0.1230,0.01364,0.00423,-0.0201,1.0000,0.0798 -1.000,-0.0966,0.01267,0.00364,-0.0199,1.0000,0.1579 -0.750,-0.0719,0.01133,0.00331,-0.0199,1.0000,0.4013 -0.500,-0.0556,0.00968,0.00319,-0.0161,1.0000,0.8417 -0.250,-0.0149,0.00945,0.00283,-0.0183,1.0000,1.0000 0.000,0.0118,0.00944,0.00264,-0.0181,1.0000,1.0000 0.250,0.0384,0.00944,0.00251,-0.0179,1.0000,1.0000 0.500,0.0650,0.00945,0.00240,-0.0177,1.0000,1.0000 0.750,0.0914,0.00948,0.00236,-0.0176,1.0000,1.0000 1.000,0.1231,0.00954,0.00236,-0.0186,0.9838,1.0000 1.250,0.1654,0.00965,0.00238,-0.0216,0.9276,1.0000 1.500,0.2036,0.00978,0.00237,-0.0233,0.8691,1.0000 1.750,0.2335,0.00997,0.00238,-0.0231,0.8203,1.0000 2.000,0.2596,0.01020,0.00243,-0.0222,0.7822,1.0000 2.250,0.2850,0.01046,0.00252,-0.0212,0.7503,1.0000 2.500,0.3106,0.01074,0.00266,-0.0202,0.7218,1.0000 2.750,0.3361,0.01103,0.00283,-0.0194,0.6951,1.0000 3.000,0.3623,0.01121,0.00300,-0.0188,0.6626,1.0000 3.250,0.3881,0.01139,0.00313,-0.0181,0.6275,1.0000 3.500,0.4139,0.01157,0.00327,-0.0174,0.5864,1.0000 3.750,0.4394,0.01180,0.00338,-0.0166,0.5380,1.0000 4.000,0.4648,0.01213,0.00351,-0.0159,0.4809,1.0000 4.250,0.4900,0.01256,0.00370,-0.0153,0.4168,1.0000 4.500,0.5152,0.01310,0.00398,-0.0148,0.3475,1.0000 4.750,0.5405,0.01375,0.00440,-0.0145,0.2795,1.0000 5.000,0.5658,0.01444,0.00486,-0.0143,0.2218,1.0000 5.250,0.5913,0.01517,0.00540,-0.0141,0.1770,1.0000 5.500,0.6169,0.01589,0.00603,-0.0139,0.1472,1.0000 5.750,0.6424,0.01663,0.00676,-0.0137,0.1233,1.0000 6.000,0.6678,0.01741,0.00754,-0.0134,0.1067,1.0000 6.250,0.6930,0.01823,0.00839,-0.0131,0.0926,1.0000 6.500,0.7182,0.01907,0.00928,-0.0128,0.0798,1.0000 6.750,0.7429,0.02013,0.01043,-0.0124,0.0712,1.0000 7.000,0.7674,0.02115,0.01154,-0.0121,0.0620,1.0000 7.250,0.7921,0.02222,0.01279,-0.0117,0.0545,1.0000 7.500,0.8157,0.02377,0.01443,-0.0112,0.0496,1.0000 7.750,0.8403,0.02496,0.01588,-0.0108,0.0432,1.0000 8.000,0.8627,0.02673,0.01770,-0.0105,0.0392,1.0000 8.250,0.8861,0.02895,0.02039,-0.0099,0.0366,1.0000 8.500,0.9083,0.03126,0.02318,-0.0094,0.0334,1.0000 8.750,0.9297,0.03270,0.02479,-0.0092,0.0301,1.0000 9.000,0.9474,0.03600,0.02844,-0.0090,0.0283,1.0000 9.250,0.9626,0.04012,0.03327,-0.0087,0.0272,1.0000 9.500,0.9720,0.04530,0.03915,-0.0088,0.0264,1.0000 9.750,0.9744,0.05136,0.04584,-0.0097,0.0260,1.0000 10.000,0.9691,0.05802,0.05301,-0.0118,0.0257,1.0000 10.250,0.9562,0.06520,0.06054,-0.0156,0.0257,1.0000 10.500,0.9372,0.07304,0.06855,-0.0225,0.0262,1.0000 10.750,0.9177,0.08419,0.07973,-0.0332,0.0268,1.0000