Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-e904-il-500000-n5 Airfoil,e904-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,72.37 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-e904-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.4723,0.09151,0.08929,-0.0367,1.0000,0.0062 -9.000,-0.4757,0.08799,0.08580,-0.0376,1.0000,0.0065 -8.750,-0.4814,0.08373,0.08159,-0.0392,0.9997,0.0062 -8.500,-0.4757,0.07741,0.07527,-0.0466,0.9965,0.0060 -8.250,-0.4714,0.07139,0.06924,-0.0552,0.9904,0.0065 -8.000,-0.4700,0.06540,0.06318,-0.0612,0.9809,0.0064 -7.750,-0.4673,0.06019,0.05788,-0.0641,0.9676,0.0065 -7.500,-0.4590,0.05481,0.05234,-0.0671,0.9576,0.0065 -7.250,-0.4460,0.04957,0.04691,-0.0696,0.9499,0.0068 -7.000,-0.4303,0.04440,0.04149,-0.0715,0.9435,0.0068 -5.500,-0.3318,0.02167,0.01657,-0.0636,0.9039,0.0033 -5.250,-0.3134,0.01912,0.01364,-0.0617,0.8993,0.0031 -5.000,-0.2914,0.01699,0.01116,-0.0603,0.8955,0.0029 -4.750,-0.2672,0.01513,0.00900,-0.0592,0.8924,0.0027 -4.500,-0.2429,0.01370,0.00735,-0.0583,0.8895,0.0026 -4.250,-0.2200,0.01252,0.00602,-0.0571,0.8864,0.0025 -4.000,-0.1974,0.01163,0.00500,-0.0560,0.8835,0.0025 -3.750,-0.1745,0.01088,0.00412,-0.0549,0.8810,0.0024 -3.500,-0.1503,0.01033,0.00342,-0.0542,0.8788,0.0025 -3.250,-0.1253,0.00997,0.00292,-0.0536,0.8767,0.0026 -3.000,-0.1000,0.00972,0.00255,-0.0531,0.8742,0.0028 -2.750,-0.0741,0.00955,0.00225,-0.0528,0.8718,0.0030 -2.500,-0.0486,0.00932,0.00204,-0.0524,0.8697,0.0199 -2.250,-0.0268,0.00870,0.00186,-0.0517,0.8676,0.1295 -1.750,-0.0088,0.00613,0.00162,-0.0451,0.8617,0.7344 -1.500,0.0147,0.00608,0.00178,-0.0439,0.8593,0.8086 -1.250,0.0410,0.00611,0.00180,-0.0436,0.8571,0.8321 -1.000,0.0673,0.00615,0.00179,-0.0433,0.8551,0.8492 -0.750,0.0935,0.00622,0.00186,-0.0428,0.8530,0.8674 -0.500,0.1187,0.00631,0.00195,-0.0421,0.8504,0.8831 -0.250,0.1434,0.00637,0.00203,-0.0414,0.8468,0.8942 0.000,0.1683,0.00642,0.00207,-0.0407,0.8429,0.9036 0.250,0.1954,0.00649,0.00212,-0.0404,0.8389,0.9106 0.500,0.2192,0.00650,0.00215,-0.0395,0.8329,0.9168 0.750,0.2467,0.00652,0.00215,-0.0393,0.8269,0.9203 1.000,0.2721,0.00651,0.00216,-0.0389,0.8193,0.9235 1.250,0.2987,0.00650,0.00213,-0.0386,0.8126,0.9263 1.500,0.3234,0.00649,0.00215,-0.0381,0.8061,0.9290 1.750,0.3511,0.00649,0.00218,-0.0382,0.8007,0.9305 2.000,0.3779,0.00650,0.00232,-0.0381,0.7944,0.9322 2.250,0.4049,0.00651,0.00238,-0.0380,0.7879,0.9339 2.500,0.4311,0.00651,0.00246,-0.0377,0.7799,0.9358 2.750,0.4561,0.00650,0.00251,-0.0372,0.7660,0.9380 3.000,0.4733,0.00654,0.00235,-0.0346,0.6880,0.9411 3.250,0.4712,0.00763,0.00255,-0.0283,0.4960,0.9457 3.500,0.4715,0.00898,0.00297,-0.0233,0.2836,0.9509 3.750,0.4752,0.01058,0.00352,-0.0194,0.0483,0.9563 4.000,0.4967,0.01135,0.00422,-0.0181,0.0060,0.9590 4.250,0.5210,0.01181,0.00485,-0.0175,0.0049,0.9615 4.500,0.5439,0.01231,0.00538,-0.0169,0.0024,0.9646 4.750,0.5651,0.01293,0.00609,-0.0158,0.0022,0.9684 5.000,0.5905,0.01363,0.00689,-0.0156,0.0018,0.9704 5.250,0.6140,0.01472,0.00811,-0.0149,0.0016,0.9731 5.500,0.6378,0.01606,0.00960,-0.0142,0.0015,0.9759 5.750,0.6636,0.01784,0.01156,-0.0136,0.0015,0.9784 6.000,0.6906,0.02001,0.01398,-0.0132,0.0015,0.9806 6.250,0.7182,0.02252,0.01680,-0.0129,0.0015,0.9823 6.500,0.7435,0.02576,0.02043,-0.0120,0.0016,0.9841 6.750,0.7653,0.02907,0.02413,-0.0109,0.0017,0.9871 7.000,0.7827,0.03277,0.02822,-0.0092,0.0017,0.9914 7.250,0.7962,0.03700,0.03285,-0.0074,0.0019,0.9963 7.500,0.8020,0.04065,0.03686,-0.0044,0.0020,1.0000 7.750,0.7976,0.04353,0.03995,0.0005,0.0020,1.0000 8.000,0.7889,0.04707,0.04372,0.0051,0.0021,1.0000 8.250,0.7751,0.05079,0.04761,0.0096,0.0022,1.0000 8.750,0.7706,0.05484,0.05192,0.0161,0.0024,1.0000 9.000,0.7681,0.05678,0.05397,0.0192,0.0025,1.0000 9.250,0.7487,0.06010,0.05742,0.0227,0.0024,1.0000 9.500,0.7515,0.06283,0.06027,0.0244,0.0027,1.0000 9.750,0.7270,0.06646,0.06400,0.0256,0.0025,1.0000 10.000,0.7095,0.07087,0.06851,0.0252,0.0025,1.0000 10.250,0.6997,0.07557,0.07330,0.0236,0.0025,1.0000 10.500,0.6771,0.08340,0.08120,0.0183,0.0024,1.0000