Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-fx77080-il-50000 Airfoil,fx77080-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,24.6822 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-fx77080-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.250,-0.5896,0.09411,0.08683,0.0215,1.0000,0.3537 -8.000,-0.5976,0.09091,0.08371,0.0212,1.0000,0.3641 -7.750,-0.7383,0.06117,0.05349,-0.0155,1.0000,0.1390 -7.500,-0.7323,0.05623,0.04835,-0.0150,1.0000,0.1373 -7.250,-0.7277,0.05130,0.04306,-0.0143,1.0000,0.1362 -7.000,-0.7216,0.04677,0.03801,-0.0131,1.0000,0.1371 -6.750,-0.7105,0.04317,0.03405,-0.0117,1.0000,0.1426 -6.500,-0.6949,0.04019,0.03077,-0.0102,1.0000,0.1490 -6.250,-0.6814,0.03669,0.02646,-0.0083,1.0000,0.1543 -6.000,-0.6620,0.03443,0.02410,-0.0070,1.0000,0.1673 -5.750,-0.6418,0.03197,0.02148,-0.0055,1.0000,0.1801 -5.500,-0.6221,0.02982,0.01904,-0.0039,1.0000,0.1993 -5.250,-0.6006,0.02792,0.01720,-0.0025,1.0000,0.2228 -5.000,-0.5802,0.02628,0.01555,-0.0009,1.0000,0.2535 -4.750,-0.5596,0.02478,0.01405,0.0008,1.0000,0.2887 -4.500,-0.5385,0.02347,0.01292,0.0024,1.0000,0.3260 -4.250,-0.5169,0.02226,0.01183,0.0040,1.0000,0.3661 -4.000,-0.4948,0.02109,0.01085,0.0056,1.0000,0.4113 -3.750,-0.4722,0.01991,0.00995,0.0072,1.0000,0.4685 -3.500,-0.4520,0.01871,0.00923,0.0097,1.0000,0.5474 -3.250,-0.4349,0.01762,0.00890,0.0140,1.0000,0.6667 -3.000,-0.3968,0.01767,0.00940,0.0173,1.0000,0.8287 -2.750,-0.2342,0.01909,0.00981,-0.0029,1.0000,0.9578 -2.500,-0.1358,0.01819,0.00835,-0.0181,1.0000,1.0000 -2.250,-0.1250,0.01758,0.00763,-0.0169,1.0000,1.0000 -2.000,-0.1128,0.01711,0.00707,-0.0154,1.0000,1.0000 -1.750,-0.0999,0.01675,0.00663,-0.0138,1.0000,1.0000 -1.500,-0.0863,0.01646,0.00625,-0.0120,1.0000,1.0000 -1.250,-0.0724,0.01623,0.00597,-0.0101,1.0000,1.0000 -1.000,-0.0583,0.01606,0.00574,-0.0081,1.0000,1.0000 -0.750,-0.0441,0.01592,0.00557,-0.0061,1.0000,1.0000 -0.500,-0.0296,0.01583,0.00545,-0.0040,1.0000,1.0000 -0.250,-0.0148,0.01578,0.00538,-0.0020,1.0000,1.0000 0.000,0.0000,0.01576,0.00536,0.0000,1.0000,1.0000 0.250,0.0149,0.01578,0.00538,0.0020,1.0000,1.0000 0.500,0.0296,0.01583,0.00545,0.0041,1.0000,1.0000 0.750,0.0442,0.01592,0.00557,0.0061,1.0000,1.0000 1.000,0.0584,0.01606,0.00574,0.0081,1.0000,1.0000 1.250,0.0725,0.01623,0.00596,0.0101,1.0000,1.0000 1.500,0.0864,0.01646,0.00625,0.0120,1.0000,1.0000 1.750,0.0999,0.01674,0.00662,0.0138,1.0000,1.0000 2.000,0.1130,0.01711,0.00707,0.0154,1.0000,1.0000 2.250,0.1251,0.01758,0.00763,0.0169,1.0000,1.0000 2.500,0.1359,0.01819,0.00835,0.0181,1.0000,1.0000 2.750,0.2344,0.01909,0.00981,0.0029,0.9576,1.0000 3.000,0.3973,0.01765,0.00938,-0.0173,0.8280,1.0000 3.250,0.4349,0.01762,0.00890,-0.0139,0.6666,1.0000 3.500,0.4520,0.01871,0.00923,-0.0097,0.5467,1.0000 3.750,0.4722,0.01991,0.00995,-0.0072,0.4682,1.0000 4.000,0.4948,0.02109,0.01085,-0.0056,0.4111,1.0000 4.250,0.5170,0.02226,0.01183,-0.0040,0.3659,1.0000 4.500,0.5385,0.02347,0.01292,-0.0024,0.3260,1.0000 4.750,0.5597,0.02479,0.01406,-0.0008,0.2888,1.0000 5.000,0.5803,0.02629,0.01556,0.0008,0.2540,1.0000 5.250,0.6006,0.02793,0.01720,0.0025,0.2228,1.0000 5.500,0.6221,0.02982,0.01905,0.0039,0.1993,1.0000 5.750,0.6418,0.03197,0.02147,0.0055,0.1802,1.0000 6.000,0.6619,0.03442,0.02411,0.0070,0.1671,1.0000 6.250,0.6811,0.03669,0.02649,0.0084,0.1540,1.0000 6.500,0.6948,0.04020,0.03079,0.0103,0.1488,1.0000 6.750,0.7104,0.04322,0.03411,0.0117,0.1427,1.0000 7.000,0.7215,0.04681,0.03806,0.0131,0.1371,1.0000 7.250,0.7273,0.05135,0.04312,0.0143,0.1361,1.0000 7.500,0.7322,0.05627,0.04839,0.0150,0.1373,1.0000 7.750,0.7380,0.06122,0.05355,0.0155,0.1389,1.0000 8.000,0.7417,0.06639,0.05889,0.0157,0.1397,1.0000 8.250,0.5906,0.09422,0.08694,-0.0215,0.3528,1.0000