Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ag09-il-50000-n5 Airfoil,ag09-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,32.9098 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-ag09-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.5785,0.11035,0.10356,0.0213,1.0000,0.0902 -8.000,-0.5778,0.10741,0.10069,0.0179,1.0000,0.0929 -7.750,-0.5782,0.10471,0.09807,0.0113,1.0000,0.0943 -7.500,-0.5711,0.10098,0.09435,0.0045,1.0000,0.0948 -7.250,-0.5610,0.09609,0.08951,0.0027,1.0000,0.0953 -7.000,-0.5502,0.09129,0.08473,0.0038,1.0000,0.0964 -6.500,-0.5127,0.07761,0.07075,-0.0112,1.0000,0.0543 -6.250,-0.4979,0.07299,0.06609,-0.0134,1.0000,0.0540 -6.000,-0.4816,0.06836,0.06139,-0.0159,1.0000,0.0536 -5.750,-0.4642,0.06383,0.05674,-0.0182,1.0000,0.0528 -5.500,-0.4447,0.05920,0.05198,-0.0208,1.0000,0.0515 -5.250,-0.4223,0.05436,0.04694,-0.0239,1.0000,0.0503 -5.000,-0.3976,0.04947,0.04176,-0.0269,1.0000,0.0495 -4.750,-0.3715,0.04472,0.03664,-0.0295,1.0000,0.0491 -4.500,-0.3439,0.04033,0.03177,-0.0316,1.0000,0.0505 -4.250,-0.3143,0.03608,0.02679,-0.0333,1.0000,0.0536 -4.000,-0.2868,0.03259,0.02280,-0.0341,1.0000,0.0557 -3.750,-0.2599,0.02995,0.01982,-0.0343,1.0000,0.0580 -3.500,-0.2320,0.02765,0.01705,-0.0344,1.0000,0.0631 -3.250,-0.2040,0.02555,0.01452,-0.0343,1.0000,0.0705 -3.000,-0.1763,0.02371,0.01236,-0.0339,1.0000,0.0768 -2.750,-0.1493,0.02238,0.01084,-0.0335,1.0000,0.0895 -2.500,-0.1224,0.02099,0.00926,-0.0329,1.0000,0.1011 -2.250,-0.0951,0.02003,0.00808,-0.0324,1.0000,0.1222 -2.000,-0.0682,0.01901,0.00706,-0.0319,1.0000,0.1428 -1.750,-0.0418,0.01816,0.00625,-0.0316,1.0000,0.1742 -1.500,-0.0156,0.01730,0.00555,-0.0313,1.0000,0.2191 -1.250,0.0098,0.01616,0.00492,-0.0311,1.0000,0.3124 -1.000,0.0349,0.01375,0.00440,-0.0293,1.0000,1.0000 -0.750,0.0606,0.01376,0.00406,-0.0288,1.0000,1.0000 -0.500,0.0859,0.01379,0.00384,-0.0283,1.0000,1.0000 -0.250,0.1109,0.01384,0.00370,-0.0278,1.0000,1.0000 0.000,0.1356,0.01390,0.00361,-0.0272,1.0000,1.0000 0.250,0.1600,0.01398,0.00359,-0.0267,1.0000,1.0000 0.500,0.1843,0.01409,0.00364,-0.0262,1.0000,1.0000 0.750,0.2083,0.01422,0.00375,-0.0258,1.0000,1.0000 1.000,0.2320,0.01439,0.00392,-0.0254,1.0000,1.0000 1.250,0.2553,0.01460,0.00416,-0.0251,1.0000,1.0000 1.500,0.2984,0.01484,0.00446,-0.0286,0.9777,1.0000 1.750,0.3495,0.01501,0.00475,-0.0332,0.9378,1.0000 2.000,0.3943,0.01514,0.00496,-0.0360,0.8899,1.0000 2.250,0.4319,0.01529,0.00513,-0.0369,0.8351,1.0000 2.500,0.4619,0.01551,0.00529,-0.0361,0.7761,1.0000 2.750,0.4871,0.01582,0.00551,-0.0343,0.7158,1.0000 3.000,0.5104,0.01622,0.00574,-0.0323,0.6552,1.0000 3.250,0.5335,0.01669,0.00602,-0.0305,0.5967,1.0000 3.500,0.5569,0.01724,0.00638,-0.0290,0.5413,1.0000 3.750,0.5805,0.01784,0.00680,-0.0278,0.4905,1.0000 4.000,0.6047,0.01848,0.00738,-0.0268,0.4437,1.0000 4.250,0.6292,0.01916,0.00797,-0.0260,0.4014,1.0000 4.500,0.6537,0.01988,0.00862,-0.0253,0.3628,1.0000 4.750,0.6786,0.02062,0.00936,-0.0247,0.3258,1.0000 5.000,0.7038,0.02142,0.01023,-0.0242,0.2903,1.0000 5.250,0.7285,0.02226,0.01109,-0.0237,0.2554,1.0000 5.500,0.7529,0.02317,0.01204,-0.0232,0.2198,1.0000 5.750,0.7765,0.02418,0.01302,-0.0227,0.1841,1.0000 6.000,0.8000,0.02536,0.01425,-0.0222,0.1469,1.0000 6.250,0.8225,0.02683,0.01572,-0.0216,0.1146,1.0000 6.500,0.8446,0.02852,0.01740,-0.0211,0.0892,1.0000 6.750,0.8669,0.03054,0.01963,-0.0202,0.0726,1.0000 7.000,0.8883,0.03273,0.02197,-0.0194,0.0618,1.0000 7.250,0.9093,0.03502,0.02447,-0.0186,0.0541,1.0000 7.500,0.9297,0.03783,0.02772,-0.0178,0.0479,1.0000 7.750,0.9487,0.04101,0.03140,-0.0170,0.0446,1.0000 8.000,0.9654,0.04425,0.03492,-0.0164,0.0421,1.0000 8.250,0.9780,0.04843,0.03961,-0.0160,0.0400,1.0000 8.500,0.9854,0.05334,0.04523,-0.0159,0.0381,1.0000 8.750,0.9872,0.05859,0.05104,-0.0163,0.0369,1.0000 9.000,0.9830,0.06424,0.05713,-0.0173,0.0364,1.0000 9.250,0.9724,0.07032,0.06353,-0.0194,0.0364,1.0000 9.500,0.9558,0.07668,0.07009,-0.0225,0.0369,1.0000 9.750,0.9378,0.08416,0.07764,-0.0284,0.0377,1.0000 10.000,0.9238,0.09278,0.08627,-0.0354,0.0386,1.0000