Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-m27-il-100000-n5 Airfoil,m27-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,41.2956 Max Cl/Cd alpha,5.5 Url,http://airfoiltools.com/polar/csv?polar=xf-m27-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.1431,0.10540,0.09995,-0.0256,0.6399,0.0432 -8.000,-0.1391,0.10348,0.09800,-0.0291,0.6369,0.0437 -7.750,-0.1379,0.10200,0.09650,-0.0325,0.6336,0.0439 -7.500,-0.1302,0.10035,0.09483,-0.0371,0.6294,0.0440 -7.250,-0.1181,0.09512,0.08962,-0.0357,0.6253,0.0445 -7.000,-0.1072,0.09131,0.08577,-0.0351,0.6218,0.0453 -6.750,-0.0968,0.08845,0.08284,-0.0358,0.6189,0.0467 -6.500,-0.0843,0.08582,0.08020,-0.0379,0.6146,0.0484 -6.250,-0.0704,0.08333,0.07768,-0.0405,0.6107,0.0504 -6.000,-0.0523,0.08159,0.07582,-0.0450,0.6072,0.0519 -5.750,-0.0299,0.08054,0.07454,-0.0501,0.6043,0.0525 -5.500,-0.0158,0.07674,0.07070,-0.0507,0.6011,0.0528 -5.250,-0.0038,0.07283,0.06685,-0.0502,0.5968,0.0536 -5.000,0.0112,0.06995,0.06393,-0.0505,0.5929,0.0549 -4.750,0.0293,0.06754,0.06142,-0.0516,0.5897,0.0573 -4.500,0.0552,0.06597,0.05963,-0.0542,0.5870,0.0609 -4.250,0.0914,0.06602,0.05933,-0.0585,0.5832,0.0620 -4.000,0.1059,0.06200,0.05535,-0.0586,0.5792,0.0625 -3.750,0.1205,0.05867,0.05202,-0.0583,0.5757,0.0634 -3.500,0.1390,0.05618,0.04942,-0.0583,0.5727,0.0648 -3.250,0.1605,0.05408,0.04716,-0.0587,0.5702,0.0667 -3.000,0.1883,0.05286,0.04582,-0.0601,0.5659,0.0713 -2.750,0.2240,0.05262,0.04521,-0.0619,0.5621,0.0737 -2.500,0.2402,0.04930,0.04189,-0.0617,0.5589,0.0747 -2.250,0.2602,0.04701,0.03950,-0.0615,0.5561,0.0760 -2.000,0.2830,0.04519,0.03751,-0.0614,0.5537,0.0779 -1.750,0.3077,0.04382,0.03608,-0.0618,0.5492,0.0802 -1.500,0.3347,0.04265,0.03473,-0.0621,0.5454,0.0834 -1.250,0.3715,0.04324,0.03483,-0.0625,0.5423,0.0867 -1.000,0.3917,0.04031,0.03184,-0.0623,0.5399,0.0879 -0.750,0.4126,0.03831,0.02976,-0.0620,0.5376,0.0906 -0.250,0.4706,0.03499,0.02592,-0.0616,0.5296,0.0604 0.000,0.4964,0.03370,0.02446,-0.0614,0.5265,0.0581 0.250,0.5245,0.03232,0.02278,-0.0610,0.5241,0.0556 0.750,0.5821,0.02983,0.01961,-0.0604,0.5182,0.0526 1.000,0.6066,0.02949,0.01931,-0.0605,0.5142,0.0544 1.250,0.6334,0.02896,0.01864,-0.0604,0.5110,0.0562 1.500,0.6621,0.02815,0.01760,-0.0604,0.5084,0.0567 1.750,0.6916,0.02735,0.01655,-0.0603,0.5063,0.0569 2.000,0.7181,0.02709,0.01622,-0.0605,0.5027,0.0575 2.250,0.7446,0.02690,0.01597,-0.0607,0.4988,0.0586 2.500,0.7729,0.02658,0.01554,-0.0609,0.4956,0.0602 2.750,0.8064,0.02632,0.01520,-0.0621,0.4929,0.0644 3.000,0.8379,0.02605,0.01482,-0.0627,0.4907,0.0696 3.250,0.8614,0.02624,0.01496,-0.0625,0.4872,0.0735 3.500,0.8809,0.02661,0.01542,-0.0617,0.4834,0.0791 3.750,0.9022,0.02676,0.01554,-0.0609,0.4802,0.0903 4.000,0.9253,0.02677,0.01553,-0.0603,0.4776,0.1177 4.250,0.9501,0.02669,0.01550,-0.0598,0.4755,0.1679 4.500,1.0724,0.02621,0.01641,-0.0803,0.4709,1.0000 4.750,1.0891,0.02703,0.01724,-0.0792,0.4671,1.0000 5.000,1.1085,0.02753,0.01771,-0.0783,0.4641,1.0000 5.250,1.1301,0.02782,0.01792,-0.0775,0.4617,1.0000 5.500,1.1538,0.02794,0.01795,-0.0769,0.4597,1.0000 5.750,1.1722,0.02850,0.01850,-0.0759,0.4568,1.0000 6.000,1.1774,0.02999,0.02013,-0.0737,0.4520,1.0000 6.250,1.1910,0.03080,0.02096,-0.0722,0.4489,1.0000 6.500,1.2093,0.03124,0.02141,-0.0711,0.4465,1.0000 6.750,1.2318,0.03142,0.02154,-0.0704,0.4445,1.0000 7.000,1.2580,0.03140,0.02146,-0.0700,0.4429,1.0000 7.250,1.2207,0.03511,0.02547,-0.0637,0.4355,1.0000 7.500,1.2232,0.03638,0.02677,-0.0611,0.4321,1.0000 7.750,1.2395,0.03682,0.02722,-0.0597,0.4300,1.0000 8.000,1.2639,0.03686,0.02726,-0.0592,0.4285,1.0000 8.250,1.2859,0.03708,0.02747,-0.0584,0.4268,1.0000 8.750,1.1820,0.04770,0.03829,-0.0474,0.4114,1.0000 10.250,0.9936,0.08704,0.07807,-0.0421,0.3556,1.0000 10.500,1.0088,0.08806,0.07914,-0.0416,0.3537,1.0000 10.750,1.0268,0.08866,0.07976,-0.0410,0.3523,1.0000 11.000,1.0471,0.08892,0.08006,-0.0405,0.3512,1.0000 11.500,1.0238,0.09837,0.08964,-0.0406,0.3380,1.0000 11.750,1.0425,0.09885,0.09018,-0.0401,0.3366,1.0000