Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-s1221-flap-il-50000 Airfoil,s1221-flap-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,31.0326 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-s1221-flap-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -5.500,-0.2854,0.10201,0.09672,-0.0057,1.0000,0.2589 -5.250,-0.2604,0.09631,0.09103,-0.0034,1.0000,0.2633 -5.000,-0.2612,0.09443,0.08927,-0.0017,1.0000,0.2694 -4.750,-0.2857,0.09550,0.09058,-0.0038,1.0000,0.2758 -4.500,-0.2748,0.09128,0.08644,-0.0004,1.0000,0.2784 -4.250,-0.2732,0.08908,0.08437,0.0016,1.0000,0.2822 -4.000,-0.2810,0.08803,0.08349,0.0027,1.0000,0.2870 -3.750,-0.1084,0.04699,0.04103,-0.0922,1.0000,0.1176 -3.500,-0.0247,0.03944,0.03282,-0.1099,1.0000,0.1150 -3.250,0.0601,0.03447,0.02675,-0.1252,1.0000,0.1182 -3.000,0.1008,0.03331,0.02558,-0.1305,0.9957,0.1228 -2.750,0.1949,0.03092,0.02287,-0.1429,0.9770,0.1473 -2.500,0.2807,0.03078,0.02395,-0.1515,0.9444,0.3128 -2.250,0.2969,0.03316,0.02677,-0.1432,0.9017,0.4174 -2.000,0.3105,0.03389,0.02763,-0.1352,0.8683,0.4712 -1.750,0.3442,0.03317,0.02676,-0.1323,0.8440,0.5194 -1.500,0.3905,0.03181,0.02512,-0.1339,0.8160,0.5514 -1.250,0.4417,0.03027,0.02329,-0.1360,0.7930,0.5738 -1.000,0.5116,0.02862,0.02118,-0.1424,0.7695,0.5947 -0.750,0.5773,0.02770,0.01973,-0.1490,0.7434,0.6106 -0.500,0.6343,0.02745,0.01903,-0.1547,0.7184,0.6238 -0.250,0.6894,0.02752,0.01868,-0.1606,0.6966,0.6363 0.000,0.7259,0.02779,0.01876,-0.1624,0.6785,0.6470 0.250,0.7657,0.02811,0.01888,-0.1653,0.6624,0.6574 0.500,0.8029,0.02856,0.01923,-0.1680,0.6480,0.6704 0.750,0.8315,0.02904,0.01965,-0.1685,0.6359,0.6827 1.000,0.8653,0.02950,0.01999,-0.1699,0.6251,0.6963 1.250,0.8951,0.03007,0.02053,-0.1708,0.6144,0.7114 1.500,0.9240,0.03071,0.02115,-0.1714,0.6057,0.7294 1.750,0.9523,0.03135,0.02178,-0.1720,0.5970,0.7498 2.000,0.9804,0.03206,0.02250,-0.1726,0.5892,0.7731 2.250,1.0040,0.03275,0.02326,-0.1724,0.5812,0.8006 2.500,1.0278,0.03312,0.02358,-0.1715,0.5754,0.8346 2.750,1.0363,0.03395,0.02468,-0.1690,0.5690,0.8727 3.000,1.0456,0.03421,0.02515,-0.1661,0.5634,1.0000 3.250,1.1102,0.03606,0.02681,-0.1758,0.5550,1.0000 3.500,1.1480,0.03812,0.02887,-0.1801,0.5475,1.0000 3.750,1.1873,0.03952,0.03012,-0.1830,0.5418,1.0000 4.000,1.2052,0.04196,0.03269,-0.1834,0.5359,1.0000 4.250,1.2241,0.04422,0.03502,-0.1836,0.5298,1.0000 4.500,1.2528,0.04579,0.03654,-0.1843,0.5249,1.0000 4.750,1.2618,0.04894,0.03988,-0.1836,0.5202,1.0000 5.000,1.2589,0.05302,0.04418,-0.1823,0.5149,1.0000 5.250,1.2734,0.05572,0.04694,-0.1820,0.5098,1.0000 5.500,1.3032,0.05734,0.04852,-0.1823,0.5053,1.0000 5.750,1.2447,0.06675,0.05827,-0.1793,0.5027,1.0000 6.000,1.1709,0.07805,0.06973,-0.1775,0.5036,1.0000 6.250,1.1371,0.08701,0.07875,-0.1791,0.5065,1.0000