Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-m13-il-500000 Airfoil,m13-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,98.0859 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-m13-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.4796,0.10991,0.10775,0.0071,1.0000,0.0151 -8.500,-0.4756,0.10656,0.10442,0.0044,1.0000,0.0151 -8.250,-0.4713,0.10309,0.10097,0.0017,1.0000,0.0152 -8.000,-0.4665,0.09950,0.09741,-0.0009,1.0000,0.0152 -7.750,-0.4605,0.09575,0.09367,-0.0041,1.0000,0.0152 -7.500,-0.4500,0.09151,0.08944,-0.0084,1.0000,0.0153 -7.250,-0.4460,0.08554,0.08349,-0.0112,1.0000,0.0155 -7.000,-0.4374,0.08225,0.08021,-0.0106,1.0000,0.0159 -6.750,-0.4253,0.07897,0.07691,-0.0126,1.0000,0.0163 -6.500,-0.4111,0.07548,0.07342,-0.0157,1.0000,0.0168 -6.250,-0.3947,0.07193,0.06985,-0.0192,1.0000,0.0177 -6.000,-0.3744,0.06811,0.06600,-0.0235,1.0000,0.0195 -5.750,-0.3411,0.06388,0.06166,-0.0309,1.0000,0.0207 -5.500,-0.3171,0.05973,0.05744,-0.0344,1.0000,0.0209 -5.250,-0.2937,0.05546,0.05308,-0.0373,1.0000,0.0209 -5.000,-0.2621,0.05041,0.04789,-0.0417,0.9876,0.0210 -4.750,-0.2354,0.04278,0.04008,-0.0469,0.9646,0.0219 -4.500,-0.2103,0.04071,0.03792,-0.0485,0.9379,0.0229 -4.250,-0.1881,0.03876,0.03581,-0.0487,0.9118,0.0248 -4.000,-0.1552,0.03647,0.03321,-0.0490,0.8901,0.0288 -3.750,-0.1285,0.03334,0.02977,-0.0491,0.8711,0.0291 -3.500,-0.1074,0.02696,0.02296,-0.0499,0.8547,0.0306 -3.250,-0.0843,0.02596,0.02185,-0.0499,0.8367,0.0322 -3.000,-0.0584,0.02444,0.02011,-0.0498,0.8202,0.0356 -2.750,-0.0306,0.02154,0.01676,-0.0496,0.8056,0.0416 -2.500,-0.0050,0.02083,0.01595,-0.0496,0.7905,0.0446 -2.250,0.0225,0.01940,0.01420,-0.0495,0.7769,0.0527 -1.500,0.1086,0.01258,0.00606,-0.0481,0.7424,0.0406 -1.250,0.1366,0.01205,0.00540,-0.0479,0.7311,0.0399 -1.000,0.1644,0.01132,0.00454,-0.0478,0.7206,0.0399 -0.750,0.1920,0.01081,0.00393,-0.0476,0.7105,0.0392 -0.500,0.2195,0.01015,0.00318,-0.0474,0.7003,0.0389 -0.250,0.2471,0.00973,0.00269,-0.0473,0.6904,0.0391 0.000,0.2748,0.00940,0.00228,-0.0472,0.6809,0.0398 0.250,0.3026,0.00916,0.00198,-0.0471,0.6711,0.0409 0.500,0.3306,0.00902,0.00180,-0.0471,0.6612,0.0420 0.750,0.3586,0.00895,0.00169,-0.0471,0.6518,0.0433 1.000,0.3866,0.00891,0.00162,-0.0471,0.6421,0.0464 1.250,0.4147,0.00887,0.00161,-0.0472,0.6317,0.0500 1.500,0.4428,0.00886,0.00162,-0.0472,0.6217,0.0633 1.750,0.4707,0.00891,0.00164,-0.0472,0.6116,0.0730 2.000,0.4987,0.00891,0.00165,-0.0472,0.6008,0.0828 2.250,0.5267,0.00891,0.00167,-0.0473,0.5894,0.0931 2.500,0.5546,0.00891,0.00172,-0.0473,0.5778,0.1102 2.750,0.5814,0.00697,0.00186,-0.0476,0.5668,1.0000 3.000,0.6088,0.00709,0.00191,-0.0475,0.5556,1.0000 3.250,0.6364,0.00719,0.00199,-0.0475,0.5443,1.0000 3.500,0.6639,0.00730,0.00208,-0.0475,0.5332,1.0000 3.750,0.6914,0.00743,0.00220,-0.0474,0.5224,1.0000 4.000,0.7188,0.00756,0.00231,-0.0474,0.5081,1.0000 4.250,0.7460,0.00771,0.00241,-0.0473,0.4897,1.0000 4.500,0.7727,0.00791,0.00252,-0.0472,0.4617,1.0000 4.750,0.7994,0.00815,0.00268,-0.0471,0.4323,1.0000 5.000,0.8258,0.00845,0.00287,-0.0470,0.3973,1.0000 5.250,0.8509,0.00901,0.00313,-0.0468,0.3253,1.0000 5.500,0.8648,0.01196,0.00455,-0.0461,0.0410,1.0000 5.750,0.8893,0.01277,0.00537,-0.0456,0.0256,1.0000 6.000,0.9147,0.01329,0.00598,-0.0452,0.0230,1.0000 6.250,0.9392,0.01393,0.00667,-0.0449,0.0200,1.0000 6.500,0.9597,0.01531,0.00819,-0.0439,0.0177,1.0000 6.750,0.9825,0.01616,0.00913,-0.0432,0.0170,1.0000 7.000,1.0046,0.01707,0.01013,-0.0424,0.0163,1.0000 7.250,1.0254,0.01821,0.01138,-0.0414,0.0155,1.0000 7.500,1.0465,0.01928,0.01252,-0.0405,0.0146,1.0000 7.750,1.0681,0.02018,0.01345,-0.0398,0.0135,1.0000 8.000,1.0881,0.02147,0.01480,-0.0388,0.0130,1.0000 8.250,1.1073,0.02315,0.01655,-0.0376,0.0125,1.0000 8.500,1.1265,0.02552,0.01905,-0.0365,0.0121,1.0000 8.750,1.1463,0.02833,0.02204,-0.0354,0.0120,1.0000 9.000,1.1665,0.03047,0.02439,-0.0342,0.0122,1.0000 18.250,0.7392,0.19971,0.19766,-0.0625,0.0123,1.0000 18.500,0.7423,0.20248,0.20044,-0.0630,0.0118,1.0000