Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-rae103-il-50000 Airfoil,rae103-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,27.7845 Max Cl/Cd alpha,4.5 Url,http://airfoiltools.com/polar/csv?polar=xf-rae103-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.5581,0.10047,0.09338,0.0121,1.0000,0.3737 -8.750,-0.6725,0.08000,0.07332,-0.0182,1.0000,0.1794 -8.500,-0.7360,0.07511,0.06831,-0.0208,1.0000,0.1723 -8.250,-0.7405,0.06687,0.05975,-0.0222,1.0000,0.1428 -8.000,-0.7545,0.06154,0.05385,-0.0212,1.0000,0.1301 -7.750,-0.7414,0.05642,0.04869,-0.0204,1.0000,0.1246 -7.500,-0.7487,0.05217,0.04347,-0.0176,1.0000,0.1164 -7.250,-0.7348,0.04793,0.03903,-0.0163,1.0000,0.1146 -7.000,-0.7240,0.04444,0.03501,-0.0142,1.0000,0.1147 -6.750,-0.7123,0.04159,0.03151,-0.0118,1.0000,0.1165 -6.500,-0.6928,0.03814,0.02802,-0.0107,1.0000,0.1204 -6.250,-0.6720,0.03527,0.02479,-0.0092,1.0000,0.1229 -6.000,-0.6505,0.03287,0.02191,-0.0075,1.0000,0.1290 -5.750,-0.6269,0.03054,0.01953,-0.0065,1.0000,0.1407 -5.500,-0.5981,0.02818,0.01709,-0.0058,1.0000,0.1533 -5.250,-0.5717,0.02618,0.01519,-0.0048,1.0000,0.1787 -5.000,-0.5473,0.02406,0.01336,-0.0034,1.0000,0.2185 -4.750,-0.5377,0.02140,0.01164,-0.0003,1.0000,0.3083 -4.500,-0.5518,0.01988,0.01256,0.0116,1.0000,0.6567 -4.250,-0.5319,0.02242,0.01499,0.0219,1.0000,0.7772 -4.000,-0.3050,0.02792,0.01864,0.0018,1.0000,0.9084 -3.750,-0.2248,0.02696,0.01713,-0.0080,1.0000,0.9456 -3.500,-0.1597,0.02562,0.01543,-0.0165,1.0000,0.9728 -3.250,-0.0973,0.02410,0.01359,-0.0250,1.0000,0.9948 -3.000,-0.0689,0.02319,0.01255,-0.0271,1.0000,1.0000 -2.750,-0.0540,0.02263,0.01194,-0.0265,1.0000,1.0000 -2.500,-0.0393,0.02212,0.01140,-0.0257,1.0000,1.0000 -2.250,-0.0250,0.02167,0.01090,-0.0248,1.0000,1.0000 -2.000,-0.0115,0.02127,0.01049,-0.0237,1.0000,1.0000 -1.750,0.0009,0.02092,0.01015,-0.0224,1.0000,1.0000 -1.500,0.0117,0.02062,0.00988,-0.0208,1.0000,1.0000 -1.250,0.0202,0.02039,0.00968,-0.0189,1.0000,1.0000 -1.000,0.0256,0.02023,0.00957,-0.0164,1.0000,1.0000 -0.750,0.0266,0.02016,0.00955,-0.0134,1.0000,1.0000 -0.500,0.0216,0.02016,0.00960,-0.0094,1.0000,1.0000 -0.250,0.0118,0.02020,0.00966,-0.0048,1.0000,1.0000 0.000,0.0000,0.02023,0.00969,0.0000,1.0000,1.0000 0.250,-0.0118,0.02020,0.00966,0.0048,1.0000,1.0000 0.500,-0.0216,0.02016,0.00960,0.0094,1.0000,1.0000 0.750,-0.0266,0.02015,0.00955,0.0134,1.0000,1.0000 1.000,-0.0256,0.02023,0.00957,0.0165,1.0000,1.0000 1.250,-0.0202,0.02038,0.00968,0.0189,1.0000,1.0000 1.500,-0.0116,0.02062,0.00987,0.0208,1.0000,1.0000 1.750,-0.0008,0.02091,0.01014,0.0224,1.0000,1.0000 2.000,0.0116,0.02126,0.01048,0.0237,1.0000,1.0000 2.250,0.0252,0.02166,0.01089,0.0248,1.0000,1.0000 2.500,0.0394,0.02212,0.01139,0.0257,1.0000,1.0000 2.750,0.0541,0.02262,0.01193,0.0265,1.0000,1.0000 3.000,0.0691,0.02318,0.01255,0.0271,1.0000,1.0000 3.250,0.0974,0.02409,0.01357,0.0250,0.9948,1.0000 3.500,0.1605,0.02563,0.01544,0.0163,0.9726,1.0000 3.750,0.2253,0.02696,0.01712,0.0080,0.9455,1.0000 4.000,0.3053,0.02791,0.01864,-0.0018,0.9082,1.0000 4.250,0.5319,0.02242,0.01499,-0.0219,0.7774,1.0000 4.500,0.5518,0.01986,0.01255,-0.0115,0.6561,1.0000 4.750,0.5376,0.02141,0.01164,0.0003,0.3077,1.0000 5.000,0.5472,0.02407,0.01336,0.0035,0.2181,1.0000 5.250,0.5717,0.02618,0.01519,0.0049,0.1785,1.0000 5.500,0.5981,0.02818,0.01709,0.0058,0.1533,1.0000 5.750,0.6269,0.03055,0.01953,0.0065,0.1406,1.0000 6.000,0.6505,0.03287,0.02191,0.0075,0.1290,1.0000 6.250,0.6720,0.03527,0.02479,0.0092,0.1230,1.0000 6.500,0.6928,0.03815,0.02803,0.0107,0.1203,1.0000 6.750,0.7125,0.04161,0.03152,0.0118,0.1166,1.0000 7.000,0.7239,0.04444,0.03502,0.0143,0.1146,1.0000 7.250,0.7350,0.04791,0.03900,0.0163,0.1146,1.0000 7.500,0.7488,0.05217,0.04346,0.0176,0.1164,1.0000 7.750,0.7414,0.05646,0.04872,0.0204,0.1247,1.0000 8.000,0.7546,0.06152,0.05383,0.0212,0.1301,1.0000 8.250,0.7417,0.06694,0.05982,0.0222,0.1430,1.0000 8.500,0.7131,0.07315,0.06644,0.0212,0.1616,1.0000 8.750,0.6726,0.08005,0.07337,0.0181,0.1796,1.0000 9.000,0.5586,0.10051,0.09342,-0.0122,0.3737,1.0000