Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca000834-il-500000-n5 Airfoil,naca000834-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,37.3639 Max Cl/Cd alpha,2 Url,http://airfoiltools.com/polar/csv?polar=xf-naca000834-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.750,-0.6428,0.10064,0.09845,0.0011,1.0000,0.0056 -9.500,-0.6442,0.09558,0.09341,-0.0018,1.0000,0.0057 -9.250,-0.6465,0.09024,0.08809,-0.0052,1.0000,0.0057 -7.250,-0.6256,0.03586,0.03320,-0.0226,1.0000,0.0057 -6.750,-0.6579,0.04119,0.03780,-0.0144,1.0000,0.0045 -6.500,-0.6539,0.03783,0.03421,-0.0118,1.0000,0.0041 -6.250,-0.6460,0.03441,0.03052,-0.0087,1.0000,0.0038 -6.000,-0.6368,0.03073,0.02648,-0.0053,1.0000,0.0034 -5.750,-0.6272,0.02521,0.02045,-0.0004,1.0000,0.0029 -5.500,-0.6120,0.02164,0.01642,0.0028,0.9999,0.0028 -5.250,-0.5846,0.01872,0.01307,0.0031,0.9982,0.0029 -5.000,-0.5557,0.01689,0.01096,0.0027,0.9964,0.0031 -4.750,-0.5261,0.01543,0.00929,0.0023,0.9949,0.0034 -4.500,-0.4973,0.01420,0.00790,0.0020,0.9926,0.0040 -4.250,-0.4676,0.01326,0.00681,0.0015,0.9903,0.0050 -4.000,-0.4386,0.01210,0.00553,0.0010,0.9882,0.0054 -3.750,-0.4088,0.01133,0.00467,0.0003,0.9858,0.0060 -3.500,-0.3794,0.01071,0.00397,-0.0002,0.9826,0.0071 -3.250,-0.3481,0.01014,0.00329,-0.0011,0.9800,0.0098 -3.000,-0.3155,0.00973,0.00278,-0.0023,0.9780,0.0143 -2.750,-0.2872,0.00927,0.00242,-0.0027,0.9735,0.0479 -2.500,-0.2622,0.00798,0.00200,-0.0030,0.9691,0.2754 -2.250,-0.2419,0.00659,0.00170,-0.0024,0.9635,0.5538 -2.000,-0.2197,0.00588,0.00160,-0.0013,0.9572,0.7123 -1.750,-0.1925,0.00565,0.00154,-0.0010,0.9519,0.7702 -1.500,-0.1652,0.00554,0.00147,-0.0009,0.9447,0.7971 -1.250,-0.1367,0.00546,0.00139,-0.0010,0.9381,0.8193 -1.000,-0.1093,0.00539,0.00135,-0.0008,0.9296,0.8385 -0.750,-0.0820,0.00535,0.00131,-0.0006,0.9206,0.8542 -0.500,-0.0544,0.00532,0.00128,-0.0004,0.9117,0.8678 -0.250,-0.0272,0.00530,0.00126,-0.0002,0.9017,0.8799 0.000,0.0000,0.00529,0.00126,0.0000,0.8911,0.8911 0.250,0.0272,0.00530,0.00126,0.0002,0.8799,0.9016 0.500,0.0544,0.00532,0.00128,0.0004,0.8677,0.9116 0.750,0.0820,0.00535,0.00131,0.0006,0.8541,0.9206 1.000,0.1093,0.00539,0.00135,0.0008,0.8385,0.9296 1.250,0.1366,0.00546,0.00139,0.0010,0.8193,0.9381 1.500,0.1651,0.00554,0.00147,0.0009,0.7970,0.9447 1.750,0.1924,0.00565,0.00154,0.0011,0.7694,0.9520 2.000,0.2197,0.00588,0.00160,0.0013,0.7122,0.9573 2.250,0.2417,0.00659,0.00170,0.0024,0.5527,0.9636 2.500,0.2623,0.00797,0.00199,0.0030,0.2773,0.9691 2.750,0.2872,0.00927,0.00242,0.0027,0.0475,0.9735 3.000,0.3157,0.00973,0.00277,0.0023,0.0142,0.9780 3.250,0.3483,0.01014,0.00328,0.0011,0.0099,0.9801 3.500,0.3794,0.01071,0.00396,0.0002,0.0071,0.9826 3.750,0.4088,0.01133,0.00467,-0.0003,0.0060,0.9860 4.000,0.4389,0.01210,0.00553,-0.0010,0.0054,0.9883 4.250,0.4679,0.01326,0.00681,-0.0015,0.0050,0.9905 4.500,0.4975,0.01420,0.00789,-0.0021,0.0040,0.9928 4.750,0.5262,0.01542,0.00929,-0.0023,0.0034,0.9951 5.000,0.5560,0.01689,0.01096,-0.0028,0.0031,0.9966 5.250,0.5849,0.01874,0.01309,-0.0031,0.0029,0.9983 5.500,0.6118,0.02162,0.01639,-0.0028,0.0028,1.0000 5.750,0.6267,0.02517,0.02040,0.0005,0.0029,1.0000 6.000,0.6365,0.03071,0.02646,0.0053,0.0034,1.0000 6.250,0.6458,0.03439,0.03049,0.0088,0.0038,1.0000 6.500,0.6538,0.03782,0.03419,0.0118,0.0041,1.0000 6.750,0.6556,0.04128,0.03788,0.0143,0.0046,1.0000 10.000,0.6431,0.10557,0.10336,-0.0038,0.0056,1.0000 10.250,0.6430,0.11028,0.10806,-0.0061,0.0056,1.0000