Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca25112-jf-50000 Airfoil,naca25112-jf Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,17.6759 Max Cl/Cd alpha,2.5 Url,http://www.airfoiltools.com/polar/csv?polar=xf-naca25112-jf-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.750,-0.4517,0.09133,0.08486,0.0130,1.0000,0.3743 -7.500,-0.4336,0.08811,0.08166,0.0156,1.0000,0.4064 -7.250,-0.4327,0.08599,0.07962,0.0184,1.0000,0.4427 -7.000,-0.3976,0.08218,0.07579,0.0212,1.0000,0.4835 -6.750,-0.3720,0.07941,0.07302,0.0244,1.0000,0.5356 -6.500,-0.3417,0.07660,0.07020,0.0277,1.0000,0.5993 -6.250,-0.3125,0.07376,0.06737,0.0297,1.0000,0.6583 -5.500,-0.4830,0.04731,0.03948,-0.0107,1.0000,0.1825 -5.250,-0.4739,0.04424,0.03611,-0.0087,1.0000,0.1769 -5.000,-0.4661,0.04169,0.03305,-0.0062,1.0000,0.1730 -4.750,-0.4567,0.03998,0.03079,-0.0036,1.0000,0.1707 -4.500,-0.4460,0.03797,0.02853,-0.0014,1.0000,0.1705 -4.250,-0.4349,0.03599,0.02654,0.0002,1.0000,0.1735 -4.000,-0.4233,0.03464,0.02511,0.0018,1.0000,0.1775 -3.750,-0.4098,0.03340,0.02363,0.0032,1.0000,0.1805 -3.500,-0.3947,0.03240,0.02230,0.0042,1.0000,0.1849 -3.250,-0.3783,0.03136,0.02111,0.0049,1.0000,0.1911 -3.000,-0.3207,0.02987,0.01930,-0.0013,0.9854,0.2062 -2.750,-0.2555,0.02829,0.01775,-0.0084,0.9691,0.2298 -2.500,-0.1894,0.02688,0.01642,-0.0153,0.9524,0.2669 -2.250,0.0152,0.02311,0.01531,-0.0393,0.9647,1.0000 -2.000,0.0972,0.02291,0.01457,-0.0501,0.9426,1.0000 -1.750,0.1591,0.02274,0.01406,-0.0569,0.9180,1.0000 -1.500,0.2046,0.02269,0.01376,-0.0603,0.8936,1.0000 -1.250,0.2378,0.02278,0.01364,-0.0612,0.8706,1.0000 -1.000,0.2621,0.02305,0.01374,-0.0606,0.8484,1.0000 -0.750,0.2851,0.02333,0.01387,-0.0597,0.8284,1.0000 -0.500,0.0507,0.00674,0.00137,0.0051,0.4333,0.6298 -0.250,0.3280,0.02405,0.01432,-0.0574,0.7933,1.0000 0.000,0.3487,0.02448,0.01464,-0.0561,0.7773,1.0000 0.250,0.3692,0.02497,0.01502,-0.0549,0.7624,1.0000 0.500,0.3895,0.02545,0.01541,-0.0536,0.7483,1.0000 0.750,0.4105,0.02586,0.01570,-0.0521,0.7357,1.0000 1.000,0.4299,0.02651,0.01631,-0.0510,0.7220,1.0000 1.250,0.4486,0.02725,0.01701,-0.0499,0.7085,1.0000 1.500,0.4680,0.02795,0.01765,-0.0487,0.6965,1.0000 1.750,0.4892,0.02841,0.01803,-0.0471,0.6860,1.0000 2.000,0.5060,0.02942,0.01906,-0.0461,0.6730,1.0000 2.250,0.5238,0.03035,0.01997,-0.0449,0.6617,1.0000 2.500,0.5453,0.03085,0.02040,-0.0433,0.6521,1.0000 2.750,0.5593,0.03217,0.02176,-0.0423,0.6397,1.0000 3.000,0.5765,0.03320,0.02280,-0.0410,0.6296,1.0000 3.250,0.5958,0.03400,0.02358,-0.0396,0.6195,1.0000 3.500,0.6067,0.03564,0.02527,-0.0384,0.6082,1.0000 3.750,0.6311,0.03603,0.02561,-0.0367,0.6001,1.0000 4.000,0.6374,0.03809,0.02777,-0.0355,0.5882,1.0000 4.250,0.6487,0.03973,0.02944,-0.0341,0.5783,1.0000 4.500,0.6679,0.04066,0.03038,-0.0327,0.5690,1.0000 4.750,0.6670,0.04335,0.03313,-0.0312,0.5581,1.0000 5.000,0.6992,0.04326,0.03305,-0.0297,0.5504,1.0000 5.250,0.6829,0.04731,0.03718,-0.0283,0.5390,1.0000 5.500,0.6974,0.04883,0.03873,-0.0268,0.5299,1.0000 5.750,0.6967,0.05166,0.04160,-0.0256,0.5202,1.0000 6.000,0.6888,0.05520,0.04516,-0.0245,0.5111,1.0000 6.250,0.7108,0.05622,0.04624,-0.0233,0.5017,1.0000 6.500,0.6759,0.06204,0.05201,-0.0227,0.4943,1.0000 6.750,0.7328,0.06034,0.05048,-0.0211,0.4833,1.0000 7.000,0.6711,0.06831,0.05831,-0.0211,0.4788,1.0000 7.250,0.6597,0.07226,0.06226,-0.0208,0.4726,1.0000 7.500,0.6741,0.07441,0.06449,-0.0202,0.4632,1.0000 7.750,0.6567,0.07910,0.06918,-0.0206,0.4599,1.0000 8.000,0.6824,0.08049,0.07065,-0.0197,0.4479,1.0000 8.250,0.6646,0.08541,0.07558,-0.0205,0.4460,1.0000 8.500,0.6568,0.08991,0.08012,-0.0214,0.4458,1.0000