Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-sc20406-il-200000-n5 Airfoil,sc20406-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,36.8457 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-sc20406-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.6885,0.08694,0.08346,0.0052,1.0000,0.0137 -8.750,-0.6936,0.08032,0.07688,-0.0003,1.0000,0.0134 -8.500,-0.6990,0.07089,0.06747,-0.0116,1.0000,0.0130 -8.250,-0.7017,0.06152,0.05791,-0.0192,1.0000,0.0126 -8.000,-0.6997,0.05260,0.04867,-0.0239,1.0000,0.0123 -7.750,-0.6890,0.04704,0.04280,-0.0262,1.0000,0.0125 -7.500,-0.6717,0.04468,0.04023,-0.0273,1.0000,0.0135 -7.250,-0.6541,0.04033,0.03554,-0.0287,1.0000,0.0144 -7.000,-0.6350,0.03458,0.02924,-0.0299,1.0000,0.0143 -6.750,-0.6126,0.02921,0.02321,-0.0307,1.0000,0.0141 -6.500,-0.5876,0.02523,0.01862,-0.0311,1.0000,0.0140 -6.250,-0.5613,0.02240,0.01532,-0.0313,1.0000,0.0141 -6.000,-0.5347,0.02024,0.01281,-0.0313,1.0000,0.0144 -5.750,-0.5080,0.01851,0.01082,-0.0313,1.0000,0.0149 -5.500,-0.4811,0.01709,0.00920,-0.0312,1.0000,0.0156 -5.250,-0.4541,0.01589,0.00782,-0.0312,1.0000,0.0167 -5.000,-0.4267,0.01493,0.00672,-0.0313,1.0000,0.0178 -4.750,-0.3992,0.01400,0.00576,-0.0316,1.0000,0.0213 -4.500,-0.3715,0.01345,0.00515,-0.0317,1.0000,0.0268 -4.250,-0.3433,0.01269,0.00436,-0.0320,1.0000,0.0366 -4.000,-0.3153,0.01221,0.00384,-0.0322,1.0000,0.0492 -3.750,-0.2876,0.01181,0.00347,-0.0324,1.0000,0.0656 -3.500,-0.2597,0.01133,0.00309,-0.0328,1.0000,0.0913 -3.250,-0.2315,0.01078,0.00273,-0.0332,1.0000,0.1366 -3.000,-0.2030,0.00999,0.00240,-0.0341,1.0000,0.2532 -2.750,-0.1743,0.00885,0.00217,-0.0352,1.0000,0.4855 -2.500,-0.1477,0.00848,0.00218,-0.0349,1.0000,0.5974 -2.250,-0.1219,0.00831,0.00220,-0.0344,1.0000,0.6568 -2.000,-0.0967,0.00821,0.00224,-0.0336,1.0000,0.7049 -1.750,-0.0718,0.00815,0.00226,-0.0327,1.0000,0.7403 -1.500,-0.0475,0.00812,0.00231,-0.0317,1.0000,0.7699 -1.250,-0.0236,0.00810,0.00236,-0.0307,1.0000,0.7963 -1.000,0.0002,0.00808,0.00241,-0.0296,1.0000,0.8148 -0.750,0.0249,0.00807,0.00243,-0.0289,1.0000,0.8283 -0.500,0.0498,0.00806,0.00247,-0.0283,1.0000,0.8404 -0.250,0.0745,0.00807,0.00253,-0.0276,1.0000,0.8522 0.000,0.0993,0.00808,0.00261,-0.0270,1.0000,0.8640 0.250,0.1237,0.00810,0.00271,-0.0264,1.0000,0.8763 0.500,0.1708,0.00800,0.00269,-0.0304,0.9827,0.8849 0.750,0.2144,0.00788,0.00263,-0.0334,0.9491,0.8942 1.000,0.2503,0.00779,0.00256,-0.0343,0.8970,0.9051 1.250,0.2753,0.00782,0.00250,-0.0327,0.8209,0.9186 1.500,0.2944,0.00810,0.00240,-0.0298,0.7020,0.9349 1.750,0.3135,0.00892,0.00238,-0.0276,0.4975,0.9564 2.000,0.3390,0.01008,0.00261,-0.0278,0.2686,1.0000 2.250,0.3664,0.01099,0.00295,-0.0284,0.1380,1.0000 2.500,0.3949,0.01156,0.00334,-0.0289,0.0904,1.0000 2.750,0.4234,0.01206,0.00372,-0.0293,0.0630,1.0000 3.000,0.4518,0.01252,0.00409,-0.0297,0.0433,1.0000 3.250,0.4801,0.01303,0.00460,-0.0299,0.0313,1.0000 3.500,0.5078,0.01381,0.00538,-0.0300,0.0229,1.0000 3.750,0.5355,0.01457,0.00630,-0.0300,0.0203,1.0000 4.000,0.5626,0.01549,0.00732,-0.0299,0.0187,1.0000 4.250,0.5895,0.01654,0.00847,-0.0297,0.0178,1.0000 4.500,0.6163,0.01777,0.00982,-0.0295,0.0171,1.0000 4.750,0.6429,0.01897,0.01114,-0.0293,0.0159,1.0000 5.000,0.6689,0.02069,0.01311,-0.0291,0.0145,1.0000 5.250,0.6952,0.02250,0.01526,-0.0288,0.0139,1.0000 5.500,0.7205,0.02497,0.01817,-0.0282,0.0134,1.0000 5.750,0.7441,0.02823,0.02198,-0.0275,0.0131,1.0000 6.000,0.7651,0.03249,0.02686,-0.0267,0.0130,1.0000 6.250,0.7828,0.03775,0.03271,-0.0258,0.0130,1.0000 6.500,0.7976,0.04359,0.03907,-0.0252,0.0132,1.0000 6.750,0.8096,0.04962,0.04551,-0.0251,0.0134,1.0000 7.000,0.8189,0.05571,0.05193,-0.0255,0.0137,1.0000 7.250,0.8253,0.06181,0.05829,-0.0265,0.0139,1.0000 7.500,0.8285,0.06794,0.06463,-0.0282,0.0142,1.0000 7.750,0.8285,0.07408,0.07090,-0.0306,0.0144,1.0000 8.000,0.8258,0.08033,0.07726,-0.0339,0.0146,1.0000 8.250,0.7144,0.07578,0.07291,-0.0285,0.0145,1.0000