Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ea61009-il-100000 Airfoil,ea61009-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,29.4776 Max Cl/Cd alpha,2.75 Url,http://airfoiltools.com/polar/csv?polar=xf-ea61009-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.6790,0.08929,0.08445,0.0087,1.0000,0.1983 -8.500,-0.6653,0.08531,0.08046,0.0100,1.0000,0.2051 -8.250,-0.7038,0.08013,0.07540,0.0031,1.0000,0.2140 -8.000,-0.6841,0.07633,0.07162,0.0054,1.0000,0.2201 -7.750,-0.7773,0.04921,0.04295,-0.0141,1.0000,0.1151 -7.500,-0.7625,0.04420,0.03759,-0.0138,1.0000,0.1086 -7.250,-0.7523,0.03859,0.03071,-0.0125,1.0000,0.0995 -7.000,-0.7338,0.03476,0.02653,-0.0121,1.0000,0.1009 -6.750,-0.7117,0.03187,0.02334,-0.0116,1.0000,0.1019 -6.500,-0.6879,0.02950,0.02069,-0.0111,1.0000,0.1030 -6.250,-0.6633,0.02775,0.01881,-0.0107,1.0000,0.1061 -6.000,-0.6379,0.02591,0.01668,-0.0102,1.0000,0.1074 -5.750,-0.6117,0.02427,0.01481,-0.0097,1.0000,0.1087 -5.500,-0.5856,0.02302,0.01333,-0.0093,1.0000,0.1117 -5.250,-0.5593,0.02169,0.01190,-0.0088,1.0000,0.1141 -5.000,-0.5335,0.02037,0.01066,-0.0084,1.0000,0.1164 -4.750,-0.5082,0.01936,0.00969,-0.0078,1.0000,0.1193 -4.500,-0.4838,0.01850,0.00884,-0.0071,1.0000,0.1232 -4.250,-0.4605,0.01770,0.00809,-0.0063,1.0000,0.1286 -4.000,-0.4388,0.01696,0.00747,-0.0053,1.0000,0.1348 -3.750,-0.4180,0.01635,0.00688,-0.0041,1.0000,0.1416 -3.500,-0.3991,0.01573,0.00636,-0.0026,1.0000,0.1524 -3.250,-0.3811,0.01506,0.00590,-0.0011,1.0000,0.1749 -3.000,-0.3678,0.01364,0.00533,0.0007,1.0000,0.2982 -2.750,-0.3613,0.01225,0.00543,0.0048,1.0000,0.5915 -2.500,-0.3492,0.01226,0.00579,0.0088,1.0000,0.7003 -2.250,-0.3362,0.01246,0.00606,0.0125,1.0000,0.7592 -2.000,-0.3230,0.01266,0.00628,0.0162,1.0000,0.7971 -1.750,-0.3091,0.01280,0.00640,0.0194,1.0000,0.8267 -1.500,-0.2966,0.01293,0.00653,0.0231,1.0000,0.8579 -1.250,-0.2826,0.01303,0.00663,0.0266,1.0000,0.8904 -1.000,-0.2594,0.01316,0.00675,0.0283,1.0000,0.9236 -0.750,-0.2026,0.01355,0.00709,0.0238,1.0000,0.9555 -0.500,-0.1182,0.01393,0.00735,0.0135,1.0000,0.9738 -0.250,0.0124,0.01395,0.00732,-0.0049,1.0000,1.0000 0.000,0.0000,0.01399,0.00735,0.0000,1.0000,1.0000 0.250,-0.0124,0.01395,0.00732,0.0049,1.0000,1.0000 0.500,0.1194,0.01392,0.00735,-0.0137,0.9736,1.0000 0.750,0.2035,0.01354,0.00707,-0.0239,0.9552,1.0000 1.000,0.2593,0.01315,0.00675,-0.0283,0.9236,1.0000 1.250,0.2823,0.01302,0.00662,-0.0265,0.8901,1.0000 1.500,0.2964,0.01293,0.00653,-0.0231,0.8579,1.0000 1.750,0.3089,0.01280,0.00640,-0.0194,0.8268,1.0000 2.000,0.3229,0.01266,0.00628,-0.0162,0.7973,1.0000 2.250,0.3360,0.01246,0.00606,-0.0125,0.7589,1.0000 2.500,0.3490,0.01226,0.00579,-0.0088,0.7001,1.0000 2.750,0.3611,0.01225,0.00542,-0.0047,0.5916,1.0000 3.000,0.3675,0.01365,0.00533,-0.0007,0.2958,1.0000 3.250,0.3809,0.01506,0.00590,0.0011,0.1749,1.0000 3.500,0.3989,0.01573,0.00636,0.0027,0.1523,1.0000 3.750,0.4179,0.01635,0.00688,0.0041,0.1415,1.0000 4.000,0.4387,0.01696,0.00747,0.0053,0.1347,1.0000 4.250,0.4604,0.01770,0.00808,0.0063,0.1286,1.0000 4.500,0.4837,0.01850,0.00884,0.0072,0.1232,1.0000 4.750,0.5082,0.01936,0.00969,0.0078,0.1193,1.0000 5.000,0.5335,0.02037,0.01065,0.0084,0.1164,1.0000 5.250,0.5593,0.02169,0.01190,0.0088,0.1141,1.0000 5.500,0.5856,0.02302,0.01333,0.0093,0.1117,1.0000 5.750,0.6118,0.02427,0.01482,0.0097,0.1087,1.0000 6.000,0.6379,0.02591,0.01669,0.0102,0.1075,1.0000 6.250,0.6634,0.02774,0.01880,0.0107,0.1061,1.0000 6.500,0.6880,0.02949,0.02068,0.0111,0.1030,1.0000 6.750,0.7118,0.03187,0.02334,0.0116,0.1019,1.0000 7.000,0.7339,0.03475,0.02653,0.0120,0.1010,1.0000 7.250,0.7524,0.03862,0.03074,0.0124,0.0995,1.0000 7.500,0.7470,0.05223,0.04662,0.0124,0.1473,1.0000 7.750,0.7774,0.04927,0.04301,0.0141,0.1151,1.0000 8.000,0.6846,0.07635,0.07164,-0.0054,0.2201,1.0000 8.250,0.7025,0.08022,0.07550,-0.0035,0.2139,1.0000 8.500,0.6673,0.08526,0.08042,-0.0098,0.2047,1.0000 8.750,0.6767,0.08938,0.08453,-0.0093,0.1981,1.0000