Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-raf26-il-200000 Airfoil,raf26-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,71.2795 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-raf26-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.4960,0.10001,0.09635,-0.0167,1.0000,0.0384 -8.750,-0.4979,0.09650,0.09289,-0.0197,1.0000,0.0401 -8.500,-0.5009,0.09313,0.08959,-0.0230,1.0000,0.0408 -8.250,-0.4222,0.07576,0.07247,-0.0275,1.0000,0.0433 -8.000,-0.4192,0.07249,0.06922,-0.0267,1.0000,0.0444 -7.750,-0.4210,0.06903,0.06580,-0.0266,1.0000,0.0454 -7.500,-0.4265,0.06560,0.06241,-0.0268,1.0000,0.0463 -7.250,-0.5103,0.07042,0.06704,-0.0363,1.0000,0.0429 -7.000,-0.5046,0.06792,0.06457,-0.0344,1.0000,0.0441 -6.750,-0.4981,0.06463,0.06126,-0.0348,1.0000,0.0456 -6.500,-0.4905,0.06063,0.05721,-0.0365,1.0000,0.0473 -6.250,-0.4813,0.05605,0.05252,-0.0388,1.0000,0.0499 -6.000,-0.4659,0.05252,0.04824,-0.0426,1.0000,0.0542 -5.750,-0.4614,0.04565,0.04156,-0.0425,1.0000,0.0562 -5.500,-0.4485,0.04306,0.03897,-0.0415,1.0000,0.0582 -5.250,-0.4342,0.04024,0.03598,-0.0408,1.0000,0.0621 -5.000,-0.4206,0.03645,0.03174,-0.0404,1.0000,0.0696 -4.750,-0.3988,0.02906,0.02349,-0.0381,1.0000,0.0400 -4.500,-0.3819,0.02465,0.01860,-0.0365,1.0000,0.0354 -4.250,-0.3621,0.02266,0.01623,-0.0350,1.0000,0.0376 -4.000,-0.3408,0.02020,0.01329,-0.0334,1.0000,0.0367 -3.750,-0.3182,0.01818,0.01088,-0.0319,1.0000,0.0366 -3.500,-0.2953,0.01677,0.00921,-0.0306,1.0000,0.0379 -3.250,-0.2728,0.01578,0.00804,-0.0293,1.0000,0.0404 -3.000,-0.2515,0.01463,0.00686,-0.0281,1.0000,0.0465 -2.750,-0.2303,0.01395,0.00612,-0.0267,1.0000,0.0522 -2.500,-0.2099,0.01324,0.00543,-0.0254,1.0000,0.0640 -2.250,-0.1896,0.01265,0.00488,-0.0241,1.0000,0.0878 -2.000,-0.1705,0.01160,0.00449,-0.0230,1.0000,0.2181 -1.750,-0.1383,0.01072,0.00466,-0.0246,0.9955,0.4871 -1.500,-0.1072,0.01008,0.00478,-0.0252,0.9895,0.6879 -1.250,-0.0396,0.00944,0.00462,-0.0332,0.9935,1.0000 -1.000,0.0026,0.00956,0.00456,-0.0365,0.9872,1.0000 -0.750,0.0451,0.00970,0.00455,-0.0399,0.9818,1.0000 -0.500,0.0843,0.00975,0.00448,-0.0425,0.9748,1.0000 -0.250,0.1256,0.00981,0.00445,-0.0455,0.9691,1.0000 0.000,0.1653,0.00977,0.00436,-0.0481,0.9612,1.0000 0.250,0.2085,0.00963,0.00417,-0.0512,0.9517,1.0000 0.500,0.2563,0.00944,0.00397,-0.0552,0.9454,1.0000 0.750,0.2944,0.00928,0.00380,-0.0572,0.9358,1.0000 1.000,0.3392,0.00901,0.00355,-0.0604,0.9270,1.0000 1.250,0.3895,0.00869,0.00328,-0.0647,0.9172,1.0000 1.500,0.4353,0.00846,0.00308,-0.0680,0.9023,1.0000 1.750,0.4758,0.00834,0.00299,-0.0703,0.8832,1.0000 2.000,0.5122,0.00832,0.00301,-0.0717,0.8642,1.0000 2.250,0.5399,0.00838,0.00310,-0.0713,0.8415,1.0000 2.500,0.5665,0.00844,0.00315,-0.0705,0.8135,1.0000 2.750,0.5908,0.00852,0.00319,-0.0691,0.7774,1.0000 3.000,0.6138,0.00866,0.00328,-0.0675,0.7333,1.0000 3.250,0.6351,0.00891,0.00336,-0.0655,0.6761,1.0000 3.500,0.6527,0.00936,0.00350,-0.0628,0.5901,1.0000 3.750,0.6600,0.01045,0.00373,-0.0583,0.4177,1.0000 4.000,0.6647,0.01233,0.00438,-0.0544,0.1786,1.0000 4.250,0.6825,0.01329,0.00496,-0.0527,0.1130,1.0000 4.500,0.7014,0.01416,0.00576,-0.0510,0.0885,1.0000 4.750,0.7174,0.01550,0.00704,-0.0487,0.0582,1.0000 5.000,0.7376,0.01640,0.00788,-0.0471,0.0436,1.0000 5.250,0.7573,0.01763,0.00918,-0.0453,0.0381,1.0000 5.500,0.7787,0.01876,0.01035,-0.0438,0.0343,1.0000 5.750,0.8000,0.02063,0.01229,-0.0425,0.0305,1.0000 6.000,0.8244,0.02240,0.01427,-0.0414,0.0288,1.0000 6.250,0.8487,0.02479,0.01698,-0.0402,0.0281,1.0000 6.500,0.8711,0.02784,0.02043,-0.0386,0.0282,1.0000 6.750,0.8896,0.03160,0.02464,-0.0365,0.0293,1.0000 7.000,0.9042,0.03546,0.02895,-0.0340,0.0298,1.0000 7.250,0.9170,0.03884,0.03276,-0.0314,0.0295,1.0000 15.750,0.6963,0.18805,0.18490,-0.0628,0.0310,1.0000 16.000,0.6940,0.19040,0.18726,-0.0657,0.0308,1.0000