Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20403-il-1000000 Airfoil,sc20403-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,46.5396 Max Cl/Cd alpha,0.25 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20403-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.6578,0.09432,0.09274,0.0200,1.0000,0.0047 -7.750,-0.6536,0.09021,0.08864,0.0170,1.0000,0.0047 -7.500,-0.6439,0.08532,0.08376,0.0115,1.0000,0.0047 -7.250,-0.6306,0.07983,0.07826,0.0042,1.0000,0.0047 -7.000,-0.6152,0.07422,0.07262,-0.0024,1.0000,0.0047 -6.750,-0.5984,0.06877,0.06711,-0.0080,1.0000,0.0048 -6.500,-0.5800,0.06346,0.06172,-0.0127,1.0000,0.0048 -6.250,-0.5602,0.05830,0.05646,-0.0167,1.0000,0.0048 -6.000,-0.5389,0.05330,0.05134,-0.0199,1.0000,0.0048 -5.750,-0.5164,0.04848,0.04637,-0.0226,1.0000,0.0048 -5.500,-0.4924,0.04385,0.04158,-0.0247,1.0000,0.0048 -5.250,-0.4679,0.03563,0.03304,-0.0282,1.0000,0.0051 -5.000,-0.4414,0.03008,0.02717,-0.0304,1.0000,0.0054 -4.750,-0.4136,0.02639,0.02321,-0.0317,1.0000,0.0058 -4.500,-0.3853,0.02351,0.02009,-0.0327,1.0000,0.0062 -4.250,-0.3559,0.02086,0.01718,-0.0334,1.0000,0.0068 -4.000,-0.3258,0.01843,0.01448,-0.0339,1.0000,0.0076 -3.750,-0.2955,0.01634,0.01203,-0.0342,1.0000,0.0087 -3.500,-0.2656,0.01475,0.01023,-0.0342,1.0000,0.0103 -3.000,-0.2029,0.00950,0.00438,-0.0341,1.0000,0.0055 -2.750,-0.1740,0.00873,0.00355,-0.0341,1.0000,0.0046 -2.500,-0.1430,0.00744,0.00210,-0.0347,1.0000,0.0046 -2.250,-0.1127,0.00668,0.00116,-0.0352,1.0000,0.0060 -2.000,-0.0840,0.00633,0.00082,-0.0353,1.0000,0.0279 -1.750,-0.0535,0.00531,0.00064,-0.0367,1.0000,0.2855 -1.500,-0.0230,0.00396,0.00062,-0.0383,1.0000,0.6914 -1.250,0.0040,0.00381,0.00061,-0.0381,1.0000,0.7443 -1.000,0.0303,0.00368,0.00065,-0.0377,1.0000,0.8000 -0.750,0.0563,0.00359,0.00069,-0.0372,1.0000,0.8354 -0.500,0.0821,0.00354,0.00072,-0.0367,1.0000,0.8589 -0.250,0.1081,0.00350,0.00075,-0.0363,1.0000,0.8777 0.000,0.1336,0.00346,0.00080,-0.0357,1.0000,0.8953 0.250,0.1587,0.00341,0.00085,-0.0350,1.0000,0.9133 0.750,0.2175,0.00652,0.00101,-0.0365,0.0661,0.9456 1.000,0.2417,0.00676,0.00110,-0.0355,0.0096,1.0000 1.250,0.2706,0.00731,0.00178,-0.0356,0.0047,1.0000 1.500,0.2990,0.00806,0.00265,-0.0355,0.0042,1.0000 1.750,0.3263,0.00969,0.00443,-0.0350,0.0044,1.0000 2.000,0.3551,0.01018,0.00497,-0.0348,0.0056,1.0000 9.250,0.8113,0.13275,0.13135,-0.0803,0.0044,1.0000 9.500,0.8145,0.13692,0.13552,-0.0820,0.0044,1.0000 9.750,0.8179,0.14101,0.13960,-0.0837,0.0044,1.0000