Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-m1-il-200000 Airfoil,m1-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,32.907 Max Cl/Cd alpha,2 Url,http://airfoiltools.com/polar/csv?polar=xf-m1-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.7096,0.09320,0.08977,0.0154,1.0000,0.0426 -8.500,-0.7131,0.08791,0.08451,0.0111,1.0000,0.0435 -8.250,-0.7187,0.08188,0.07852,0.0048,1.0000,0.0441 -8.000,-0.7199,0.07546,0.07202,-0.0011,1.0000,0.0452 -7.750,-0.7212,0.06876,0.06491,-0.0078,1.0000,0.0478 -7.500,-0.6682,0.05024,0.04657,-0.0131,1.0000,0.0501 -7.250,-0.6579,0.04679,0.04312,-0.0124,1.0000,0.0518 -7.000,-0.6499,0.04281,0.03904,-0.0123,1.0000,0.0544 -6.750,-0.6414,0.03992,0.03531,-0.0122,1.0000,0.0611 -6.500,-0.6745,0.04549,0.04048,-0.0102,1.0000,0.0628 -6.250,-0.6563,0.04243,0.03751,-0.0100,1.0000,0.0658 -6.000,-0.6391,0.03932,0.03384,-0.0096,1.0000,0.0763 -5.750,-0.6198,0.03735,0.03161,-0.0093,1.0000,0.0894 -5.500,-0.5908,0.02774,0.02091,-0.0066,1.0000,0.0462 -5.250,-0.5667,0.02409,0.01680,-0.0057,1.0000,0.0442 -5.000,-0.5408,0.02184,0.01415,-0.0048,1.0000,0.0455 -4.750,-0.5140,0.02080,0.01272,-0.0041,1.0000,0.0481 -4.500,-0.4882,0.01829,0.00997,-0.0035,1.0000,0.0495 -4.250,-0.4628,0.01670,0.00837,-0.0030,1.0000,0.0531 -4.000,-0.4366,0.01584,0.00745,-0.0026,1.0000,0.0577 -3.750,-0.4106,0.01492,0.00646,-0.0020,1.0000,0.0601 -3.500,-0.3858,0.01381,0.00535,-0.0014,1.0000,0.0640 -3.250,-0.3604,0.01311,0.00468,-0.0009,1.0000,0.0694 -3.000,-0.3346,0.01253,0.00406,-0.0004,1.0000,0.0740 -2.750,-0.3092,0.01184,0.00340,0.0000,1.0000,0.0829 -2.500,-0.2843,0.01093,0.00282,0.0005,1.0000,0.1379 -2.250,-0.2717,0.00828,0.00249,0.0027,1.0000,0.6546 -2.000,-0.2547,0.00774,0.00257,0.0062,1.0000,0.8214 -1.750,-0.2266,0.00770,0.00266,0.0074,1.0000,0.9188 -1.500,-0.1685,0.00786,0.00274,0.0018,1.0000,0.9789 -1.250,-0.1058,0.00794,0.00267,-0.0056,1.0000,1.0000 -1.000,-0.0838,0.00783,0.00250,-0.0047,1.0000,1.0000 -0.750,-0.0622,0.00774,0.00237,-0.0037,1.0000,1.0000 -0.500,-0.0409,0.00768,0.00227,-0.0026,1.0000,1.0000 -0.250,-0.0202,0.00764,0.00222,-0.0014,1.0000,1.0000 0.000,0.0000,0.00763,0.00220,0.0000,1.0000,1.0000 0.250,0.0202,0.00764,0.00222,0.0014,1.0000,1.0000 0.500,0.0409,0.00768,0.00227,0.0026,1.0000,1.0000 0.750,0.0622,0.00774,0.00237,0.0037,1.0000,1.0000 1.000,0.0838,0.00782,0.00250,0.0047,1.0000,1.0000 1.250,0.1058,0.00794,0.00267,0.0056,1.0000,1.0000 1.500,0.1685,0.00786,0.00274,-0.0018,0.9789,1.0000 1.750,0.2266,0.00770,0.00266,-0.0074,0.9187,1.0000 2.000,0.2547,0.00774,0.00257,-0.0062,0.8216,1.0000 2.250,0.2717,0.00828,0.00249,-0.0027,0.6540,1.0000 2.500,0.2843,0.01094,0.00282,-0.0005,0.1369,1.0000 2.750,0.3092,0.01184,0.00340,0.0000,0.0829,1.0000 3.000,0.3346,0.01253,0.00406,0.0004,0.0740,1.0000 3.250,0.3604,0.01311,0.00468,0.0009,0.0694,1.0000 3.500,0.3858,0.01381,0.00535,0.0014,0.0640,1.0000 3.750,0.4106,0.01493,0.00646,0.0020,0.0601,1.0000 4.000,0.4367,0.01584,0.00745,0.0026,0.0577,1.0000 4.250,0.4628,0.01670,0.00837,0.0030,0.0531,1.0000 4.500,0.4882,0.01828,0.00996,0.0035,0.0495,1.0000 4.750,0.5140,0.02081,0.01274,0.0041,0.0481,1.0000 5.000,0.5408,0.02184,0.01415,0.0048,0.0455,1.0000 5.250,0.5667,0.02410,0.01680,0.0056,0.0442,1.0000 5.500,0.5908,0.02774,0.02091,0.0066,0.0462,1.0000 8.750,0.7101,0.09324,0.08981,-0.0156,0.0426,1.0000 9.000,0.7086,0.09804,0.09460,-0.0187,0.0416,1.0000 9.250,0.7088,0.10241,0.09895,-0.0210,0.0404,1.0000 9.500,0.7119,0.10604,0.10257,-0.0219,0.0389,1.0000 12.250,0.5762,0.14251,0.13907,-0.0210,0.0355,1.0000 12.500,0.5711,0.14527,0.14182,-0.0234,0.0349,1.0000