Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ames02-il-200000 Airfoil,ames02-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,37.338 Max Cl/Cd alpha,5.25 Url,http://airfoiltools.com/polar/csv?polar=xf-ames02-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.6981,0.09587,0.09243,0.0223,1.0000,0.0497 -8.250,-0.7058,0.08920,0.08580,0.0155,1.0000,0.0510 -8.000,-0.7408,0.07609,0.07235,-0.0025,1.0000,0.0520 -7.750,-0.7255,0.07315,0.06956,-0.0009,1.0000,0.0525 -7.500,-0.7143,0.07041,0.06682,-0.0005,1.0000,0.0535 -7.250,-0.7072,0.06596,0.06226,-0.0025,1.0000,0.0555 -7.000,-0.7054,0.05887,0.05479,-0.0063,1.0000,0.0586 -6.750,-0.6895,0.05603,0.05194,-0.0064,1.0000,0.0602 -6.500,-0.6784,0.05073,0.04619,-0.0080,1.0000,0.0651 -6.250,-0.6592,0.04802,0.04348,-0.0081,1.0000,0.0673 -6.000,-0.6418,0.04404,0.03914,-0.0088,1.0000,0.0730 -5.750,-0.6207,0.03115,0.02429,-0.0071,1.0000,0.0419 -5.500,-0.5960,0.02831,0.02134,-0.0072,1.0000,0.0426 -5.250,-0.5692,0.02530,0.01796,-0.0068,1.0000,0.0404 -5.000,-0.5417,0.02259,0.01482,-0.0063,1.0000,0.0395 -4.750,-0.5137,0.02067,0.01262,-0.0060,1.0000,0.0399 -4.500,-0.4854,0.01923,0.01089,-0.0057,1.0000,0.0414 -4.250,-0.4577,0.01804,0.00972,-0.0057,1.0000,0.0441 -4.000,-0.4294,0.01693,0.00848,-0.0055,1.0000,0.0463 -3.750,-0.4019,0.01579,0.00742,-0.0054,1.0000,0.0489 -3.500,-0.3742,0.01490,0.00656,-0.0053,1.0000,0.0535 -3.250,-0.3466,0.01406,0.00579,-0.0053,1.0000,0.0594 -3.000,-0.3189,0.01327,0.00510,-0.0053,1.0000,0.0676 -2.750,-0.2911,0.01250,0.00444,-0.0054,1.0000,0.0828 -2.500,-0.2637,0.01144,0.00375,-0.0056,1.0000,0.1387 -2.250,-0.2430,0.00915,0.00334,-0.0054,1.0000,0.5400 -2.000,-0.2207,0.00858,0.00338,-0.0039,1.0000,0.6930 -1.750,-0.1980,0.00834,0.00337,-0.0022,1.0000,0.7708 -1.500,-0.1771,0.00816,0.00337,-0.0001,1.0000,0.8297 -1.250,-0.1573,0.00807,0.00342,0.0024,1.0000,0.8856 -1.000,-0.1267,0.00809,0.00349,0.0026,1.0000,0.9451 -0.750,-0.0702,0.00817,0.00352,-0.0029,1.0000,0.9894 -0.500,-0.0384,0.00816,0.00345,-0.0044,1.0000,1.0000 -0.250,-0.0252,0.00823,0.00344,-0.0025,1.0000,1.0000 0.000,-0.0018,0.00833,0.00349,-0.0022,0.9986,1.0000 0.250,0.0514,0.00827,0.00340,-0.0075,0.9883,1.0000 0.500,0.1008,0.00823,0.00333,-0.0119,0.9747,1.0000 0.750,0.1397,0.00823,0.00332,-0.0138,0.9559,1.0000 1.000,0.1666,0.00830,0.00337,-0.0130,0.9342,1.0000 1.250,0.1874,0.00837,0.00341,-0.0109,0.9107,1.0000 1.500,0.2071,0.00842,0.00342,-0.0084,0.8869,1.0000 1.750,0.2282,0.00844,0.00340,-0.0062,0.8605,1.0000 2.000,0.2497,0.00845,0.00335,-0.0041,0.8305,1.0000 2.250,0.2727,0.00846,0.00329,-0.0023,0.7918,1.0000 2.500,0.2960,0.00853,0.00321,-0.0006,0.7386,1.0000 2.750,0.3196,0.00876,0.00314,0.0010,0.6541,1.0000 3.000,0.3435,0.00939,0.00313,0.0022,0.5162,1.0000 3.250,0.3693,0.01033,0.00334,0.0022,0.3660,1.0000 3.500,0.3962,0.01117,0.00368,0.0020,0.2666,1.0000 3.750,0.4237,0.01185,0.00405,0.0017,0.2073,1.0000 4.000,0.4512,0.01251,0.00445,0.0015,0.1689,1.0000 4.250,0.4787,0.01311,0.00492,0.0014,0.1419,1.0000 4.500,0.5060,0.01378,0.00545,0.0014,0.1224,1.0000 4.750,0.5334,0.01439,0.00599,0.0014,0.1072,1.0000 5.000,0.5606,0.01504,0.00656,0.0014,0.0954,1.0000 5.250,0.5877,0.01574,0.00722,0.0014,0.0859,1.0000 5.500,0.6146,0.01647,0.00792,0.0015,0.0779,1.0000 5.750,0.6413,0.01727,0.00869,0.0016,0.0713,1.0000 6.000,0.6679,0.01816,0.00956,0.0018,0.0659,1.0000 6.250,0.6942,0.01908,0.01041,0.0019,0.0612,1.0000 6.500,0.7210,0.01996,0.01140,0.0021,0.0571,1.0000 6.750,0.7473,0.02120,0.01273,0.0023,0.0540,1.0000 7.000,0.7735,0.02219,0.01372,0.0025,0.0510,1.0000 7.250,0.7993,0.02365,0.01545,0.0028,0.0483,1.0000 7.500,0.8249,0.02499,0.01688,0.0030,0.0464,1.0000 7.750,0.8495,0.02693,0.01901,0.0032,0.0451,1.0000 8.000,0.8723,0.02930,0.02194,0.0037,0.0434,1.0000 8.250,0.8960,0.03072,0.02345,0.0039,0.0417,1.0000 8.500,0.9175,0.03311,0.02602,0.0042,0.0407,1.0000 8.750,0.9328,0.03719,0.03078,0.0049,0.0405,1.0000 9.000,0.9441,0.04185,0.03599,0.0055,0.0406,1.0000 9.250,0.9529,0.04665,0.04122,0.0060,0.0411,1.0000 9.500,0.7785,0.09488,0.09124,-0.0202,0.0735,1.0000 9.750,0.7689,0.10154,0.09785,-0.0255,0.0713,1.0000