Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-cap21c-il-50000 Airfoil,cap21c-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,9.90467 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-cap21c-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -10.000,-0.5023,0.13312,0.12483,0.0354,1.0005,0.3214 -9.750,-0.4690,0.12766,0.11935,0.0360,1.0005,0.3274 -9.500,-0.4891,0.12707,0.11881,0.0347,1.0005,0.3368 -9.250,-0.4537,0.12169,0.11343,0.0354,1.0005,0.3436 -9.000,-0.4587,0.11959,0.11139,0.0348,1.0005,0.3539 -8.750,-0.4565,0.11768,0.10951,0.0349,1.0005,0.3668 -8.500,-0.4283,0.11315,0.10503,0.0353,1.0005,0.3755 -8.250,-0.4283,0.11070,0.10263,0.0350,1.0005,0.3859 -8.000,-0.4406,0.10977,0.10176,0.0350,1.0005,0.3986 -7.750,-0.4022,0.10475,0.09678,0.0353,1.0005,0.4073 -7.500,-0.3947,0.10205,0.09414,0.0355,1.0005,0.4193 -7.000,-0.3768,0.09701,0.08924,0.0364,1.0005,0.4486 -6.500,-0.3594,0.09218,0.08453,0.0374,1.0005,0.4782 -6.000,-0.3353,0.08717,0.07971,0.0386,1.0005,0.5091 -5.750,-0.3136,0.08431,0.07695,0.0391,1.0005,0.5269 -5.500,-0.2948,0.08188,0.07464,0.0399,1.0005,0.5481 -5.250,-0.2929,0.08031,0.07323,0.0415,1.0005,0.5703 -5.000,-0.2657,0.07721,0.07030,0.0415,1.0005,0.5886 -4.750,-0.2438,0.07470,0.06801,0.0417,1.0005,0.6092 -4.500,-0.2313,0.07274,0.06633,0.0426,1.0005,0.6334 -4.250,-0.1927,0.07024,0.06393,0.0403,0.7549,0.6647 -4.000,-0.1854,0.07008,0.06280,0.0447,0.6237,0.6932 -3.750,-0.3931,0.04886,0.04170,0.0103,1.0005,0.3813 -3.500,-0.3786,0.04594,0.03895,0.0092,1.0005,0.3782 -3.250,-0.2735,0.04133,0.03330,-0.0090,0.6796,0.3809 -3.000,-0.2533,0.03969,0.03083,-0.0098,0.6155,0.3826 -2.750,-0.2295,0.03840,0.02911,-0.0102,0.5797,0.3843 -2.500,-0.2034,0.03733,0.02773,-0.0105,0.5553,0.3863 -2.250,-0.1764,0.03647,0.02668,-0.0109,0.5364,0.3905 -2.000,-0.1486,0.03551,0.02545,-0.0118,0.5207,0.3953 -1.750,-0.1199,0.03457,0.02422,-0.0130,0.5069,0.3990 -1.500,-0.0920,0.03399,0.02356,-0.0131,0.4950,0.4024 -1.250,-0.0630,0.03347,0.02297,-0.0136,0.4849,0.4062 -1.000,-0.0338,0.03307,0.02242,-0.0143,0.4762,0.4114 -0.750,-0.0056,0.03280,0.02208,-0.0144,0.4674,0.4174 -0.500,0.0225,0.03268,0.02199,-0.0147,0.4588,0.4241 -0.250,0.0514,0.03260,0.02170,-0.0150,0.4512,0.4304 0.000,0.0796,0.03267,0.02195,-0.0153,0.4451,0.4362 0.250,0.1084,0.03283,0.02206,-0.0157,0.4391,0.4435 0.500,0.1357,0.03310,0.02238,-0.0155,0.4333,0.4520 0.750,0.1630,0.03350,0.02291,-0.0159,0.4266,0.4622 1.000,0.1896,0.03388,0.02330,-0.0155,0.4208,0.4728 1.250,0.2160,0.03456,0.02417,-0.0156,0.4167,0.4838 1.500,0.2424,0.03538,0.02523,-0.0161,0.4125,0.4963 1.750,0.2682,0.03611,0.02610,-0.0160,0.4074,0.5123 2.000,0.2928,0.03692,0.02707,-0.0156,0.4025,0.5339 2.250,0.3146,0.03815,0.02876,-0.0159,0.3983,0.5599 2.500,0.3351,0.03944,0.03055,-0.0159,0.3961,0.5992 2.750,0.3497,0.04039,0.03229,-0.0141,0.3936,0.6786 3.000,0.4156,0.04196,0.03436,-0.0197,0.3865,0.9995 3.250,0.4262,0.04471,0.03708,-0.0203,0.3846,0.9995 3.500,0.4374,0.04771,0.04007,-0.0210,0.3855,0.9995 3.750,0.4481,0.05093,0.04329,-0.0218,0.3867,0.9995 4.000,0.4583,0.05427,0.04662,-0.0228,0.3877,0.9995 4.250,0.2777,0.07521,0.06861,-0.0564,0.6369,0.9995 4.500,0.2816,0.07650,0.06967,-0.0545,0.6106,0.9995 4.750,0.3091,0.07947,0.07243,-0.0547,0.5917,0.9995 5.000,0.3211,0.08180,0.07460,-0.0538,0.5722,0.9995 5.250,0.3306,0.08366,0.07633,-0.0525,0.5495,0.9995 5.500,0.3548,0.08649,0.07903,-0.0521,0.5303,0.9995 5.750,0.3798,0.08966,0.08209,-0.0517,0.5131,0.9995 6.000,0.3929,0.09222,0.08458,-0.0511,0.4975,0.9995 6.250,0.4015,0.09454,0.08681,-0.0504,0.4824,0.9995 6.750,0.4110,0.09896,0.09108,-0.0493,0.4539,0.9995 7.000,0.4173,0.10141,0.09346,-0.0489,0.4402,0.9995 7.250,0.4256,0.10400,0.09598,-0.0485,0.4269,0.9995 7.500,0.4382,0.10696,0.09888,-0.0483,0.4152,0.9995 7.750,0.4640,0.11057,0.10245,-0.0480,0.4048,0.9995 8.000,0.4551,0.11225,0.10408,-0.0481,0.3934,0.9995 8.250,0.4735,0.11612,0.10789,-0.0481,0.3867,0.9995