Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ma409-il-1000000 Airfoil,ma409-il Reynolds number,1000000 Ncrit,9 Mach,0 Max Cl/Cd,110.64 Max Cl/Cd alpha,1.25 Url,http://airfoiltools.com/polar/csv?polar=xf-ma409-il-1000000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.4269,0.02887,0.02563,-0.0954,0.7470,0.0070 -8.500,-0.4053,0.02355,0.01978,-0.0991,0.7465,0.0071 -8.250,-0.3820,0.02006,0.01584,-0.1007,0.7457,0.0072 -8.000,-0.3567,0.01793,0.01338,-0.1013,0.7445,0.0071 -7.750,-0.3312,0.01591,0.01104,-0.1016,0.7430,0.0071 -7.500,-0.3057,0.01383,0.00863,-0.1019,0.7417,0.0074 -7.250,-0.2791,0.01266,0.00727,-0.1020,0.7409,0.0080 -7.000,-0.2519,0.01199,0.00648,-0.1020,0.7404,0.0087 -6.750,-0.2244,0.01139,0.00576,-0.1020,0.7397,0.0094 -6.500,-0.1968,0.01085,0.00510,-0.1019,0.7387,0.0100 -6.250,-0.1691,0.01039,0.00453,-0.1019,0.7378,0.0106 -5.750,-0.1134,0.00931,0.00319,-0.1018,0.7363,0.0132 -5.500,-0.0854,0.00891,0.00272,-0.1017,0.7353,0.0155 -5.250,-0.0573,0.00864,0.00237,-0.1017,0.7341,0.0176 -5.000,-0.0295,0.00826,0.00216,-0.1016,0.7325,0.0476 -4.750,-0.0015,0.00820,0.00212,-0.1016,0.7307,0.0575 -4.500,0.0267,0.00825,0.00216,-0.1016,0.7292,0.0601 -4.250,0.0546,0.00805,0.00194,-0.1016,0.7278,0.0651 -4.000,0.0827,0.00796,0.00185,-0.1016,0.7264,0.0687 -3.750,0.1108,0.00794,0.00179,-0.1015,0.7248,0.0721 -3.500,0.1389,0.00787,0.00169,-0.1015,0.7232,0.0751 -3.250,0.1669,0.00769,0.00154,-0.1015,0.7216,0.0812 -3.000,0.1951,0.00758,0.00143,-0.1015,0.7200,0.0849 -2.750,0.2232,0.00748,0.00133,-0.1015,0.7181,0.0888 -2.500,0.2513,0.00735,0.00123,-0.1015,0.7161,0.0998 -2.250,0.2792,0.00717,0.00118,-0.1016,0.7137,0.1373 -2.000,0.3069,0.00702,0.00115,-0.1016,0.7102,0.1836 -1.750,0.3347,0.00674,0.00111,-0.1016,0.7057,0.2547 -1.500,0.3625,0.00661,0.00108,-0.1016,0.7005,0.2971 -1.250,0.3903,0.00650,0.00106,-0.1016,0.6959,0.3298 -1.000,0.4184,0.00635,0.00103,-0.1016,0.6888,0.3652 -0.750,0.4464,0.00615,0.00102,-0.1017,0.6783,0.4257 -0.500,0.4708,0.00623,0.00089,-0.1010,0.5843,0.4700 -0.250,0.4965,0.00622,0.00104,-0.1008,0.5696,0.5573 0.000,0.5164,0.00549,0.00121,-0.0990,0.5628,0.8926 0.250,0.5480,0.00547,0.00127,-0.0998,0.5546,1.0000 0.500,0.5755,0.00557,0.00136,-0.0997,0.5460,1.0000 0.750,0.6029,0.00568,0.00143,-0.0996,0.5357,1.0000 1.000,0.6306,0.00575,0.00147,-0.0995,0.5123,1.0000 1.250,0.6572,0.00594,0.00149,-0.0993,0.4681,1.0000 1.500,0.6822,0.00629,0.00162,-0.0988,0.4162,1.0000 1.750,0.7058,0.00681,0.00182,-0.0982,0.3438,1.0000 2.000,0.7314,0.00712,0.00199,-0.0978,0.3120,1.0000 2.250,0.7533,0.00789,0.00227,-0.0970,0.2037,1.0000 2.500,0.7739,0.00889,0.00270,-0.0959,0.0892,1.0000 2.750,0.7965,0.00972,0.00318,-0.0950,0.0172,1.0000 3.000,0.8227,0.00999,0.00351,-0.0947,0.0154,1.0000 3.250,0.8485,0.01033,0.00390,-0.0943,0.0136,1.0000 3.500,0.8731,0.01088,0.00454,-0.0936,0.0113,1.0000 3.750,0.8972,0.01151,0.00525,-0.0928,0.0103,1.0000 4.000,0.9223,0.01194,0.00571,-0.0923,0.0099,1.0000 4.250,0.9469,0.01244,0.00629,-0.0917,0.0094,1.0000 4.500,0.9709,0.01302,0.00692,-0.0910,0.0087,1.0000 4.750,0.9943,0.01367,0.00762,-0.0902,0.0080,1.0000 5.000,1.0169,0.01444,0.00844,-0.0892,0.0075,1.0000 5.250,1.0383,0.01543,0.00949,-0.0881,0.0072,1.0000 5.500,1.0592,0.01659,0.01073,-0.0867,0.0071,1.0000 5.750,1.0801,0.01780,0.01200,-0.0856,0.0068,1.0000 6.000,1.0991,0.01994,0.01421,-0.0842,0.0064,1.0000 6.250,1.1207,0.02168,0.01607,-0.0831,0.0064,1.0000 6.500,1.1421,0.02350,0.01803,-0.0819,0.0064,1.0000 6.750,1.1623,0.02566,0.02037,-0.0807,0.0064,1.0000 7.000,1.1791,0.02885,0.02382,-0.0789,0.0063,1.0000 7.250,1.1873,0.03421,0.02963,-0.0758,0.0062,1.0000 7.500,1.1976,0.03611,0.03188,-0.0731,0.0061,1.0000 7.750,1.2123,0.03725,0.03325,-0.0711,0.0058,1.0000 9.500,1.0451,0.05725,0.05486,-0.0355,0.0062,1.0000 9.750,1.0218,0.06167,0.05942,-0.0343,0.0062,1.0000 10.000,0.9978,0.06683,0.06470,-0.0343,0.0062,1.0000 10.250,0.9735,0.07256,0.07054,-0.0351,0.0062,1.0000 10.500,0.9489,0.07913,0.07723,-0.0374,0.0062,1.0000