Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca000834-il-1000000-n5 Airfoil,naca000834-il Reynolds number,1000000 Ncrit,5 Mach,0 Max Cl/Cd,42.7702 Max Cl/Cd alpha,4 Url,http://airfoiltools.com/polar/csv?polar=xf-naca000834-il-1000000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.6414,0.07735,0.07582,-0.0176,1.0000,0.0052 -8.500,-0.6508,0.07219,0.07059,-0.0209,1.0000,0.0052 -8.250,-0.6588,0.06787,0.06620,-0.0215,1.0000,0.0052 -8.000,-0.6612,0.06339,0.06162,-0.0219,1.0000,0.0052 -7.750,-0.6612,0.05906,0.05717,-0.0217,1.0000,0.0052 -7.500,-0.6589,0.05489,0.05286,-0.0209,1.0000,0.0053 -7.250,-0.6549,0.05091,0.04872,-0.0196,1.0000,0.0053 -7.000,-0.6497,0.04713,0.04477,-0.0178,1.0000,0.0053 -6.750,-0.6442,0.04361,0.04108,-0.0154,1.0000,0.0053 -6.500,-0.6381,0.04030,0.03758,-0.0126,1.0000,0.0053 -5.750,-0.5868,0.02918,0.02565,-0.0096,0.9953,0.0053 -5.500,-0.5705,0.02353,0.01952,-0.0086,0.9920,0.0042 -5.250,-0.5444,0.02018,0.01580,-0.0080,0.9896,0.0037 -5.000,-0.5160,0.01706,0.01231,-0.0076,0.9879,0.0033 -4.750,-0.4868,0.01405,0.00892,-0.0071,0.9864,0.0028 -4.500,-0.4615,0.01181,0.00647,-0.0061,0.9830,0.0025 -4.250,-0.4357,0.01039,0.00486,-0.0055,0.9793,0.0024 -4.000,-0.4075,0.00952,0.00385,-0.0057,0.9765,0.0022 -3.750,-0.3814,0.00897,0.00319,-0.0054,0.9711,0.0022 -3.500,-0.3530,0.00855,0.00267,-0.0056,0.9669,0.0022 -3.250,-0.3255,0.00824,0.00228,-0.0056,0.9617,0.0023 -3.000,-0.2979,0.00801,0.00197,-0.0055,0.9556,0.0026 -2.750,-0.2704,0.00782,0.00178,-0.0055,0.9492,0.0047 -2.500,-0.2435,0.00767,0.00164,-0.0054,0.9415,0.0101 -2.250,-0.2164,0.00758,0.00144,-0.0054,0.9332,0.0048 -2.000,-0.1899,0.00743,0.00132,-0.0052,0.9238,0.0147 -1.750,-0.1706,0.00619,0.00099,-0.0041,0.9123,0.2852 -1.500,-0.1487,0.00546,0.00082,-0.0033,0.9003,0.4495 -1.250,-0.1266,0.00485,0.00070,-0.0024,0.8885,0.5927 -1.000,-0.1034,0.00447,0.00065,-0.0016,0.8768,0.6926 -0.750,-0.0795,0.00423,0.00063,-0.0008,0.8647,0.7638 -0.500,-0.0532,0.00417,0.00061,-0.0005,0.8522,0.7894 -0.250,-0.0267,0.00414,0.00060,-0.0002,0.8389,0.8084 0.000,0.0000,0.00413,0.00059,0.0000,0.8245,0.8245 0.250,0.0266,0.00414,0.00060,0.0002,0.8084,0.8390 0.500,0.0532,0.00417,0.00061,0.0005,0.7894,0.8522 0.750,0.0794,0.00423,0.00063,0.0008,0.7637,0.8647 1.000,0.1033,0.00447,0.00065,0.0016,0.6907,0.8768 1.250,0.1266,0.00484,0.00070,0.0024,0.5947,0.8886 1.500,0.1485,0.00547,0.00082,0.0033,0.4466,0.9004 1.750,0.1705,0.00620,0.00099,0.0041,0.2833,0.9123 2.000,0.1898,0.00743,0.00132,0.0052,0.0142,0.9239 2.250,0.2163,0.00758,0.00144,0.0054,0.0048,0.9333 2.500,0.2434,0.00767,0.00164,0.0055,0.0106,0.9417 2.750,0.2703,0.00782,0.00178,0.0055,0.0048,0.9494 3.000,0.2978,0.00800,0.00196,0.0056,0.0026,0.9557 3.250,0.3254,0.00824,0.00228,0.0056,0.0023,0.9618 3.500,0.3531,0.00855,0.00268,0.0056,0.0022,0.9670 3.750,0.3815,0.00897,0.00319,0.0054,0.0022,0.9713 4.000,0.4076,0.00953,0.00386,0.0057,0.0023,0.9765 4.250,0.4358,0.01039,0.00487,0.0055,0.0024,0.9793 4.500,0.4616,0.01182,0.00647,0.0061,0.0025,0.9830 4.750,0.4868,0.01404,0.00891,0.0071,0.0028,0.9864 5.000,0.5160,0.01705,0.01231,0.0076,0.0033,0.9879 5.250,0.5445,0.02018,0.01580,0.0080,0.0037,0.9896 5.500,0.5705,0.02355,0.01954,0.0086,0.0043,0.9920 5.750,0.5869,0.02917,0.02564,0.0095,0.0052,0.9953 6.000,0.6091,0.03309,0.02987,0.0097,0.0053,0.9974 6.250,0.6301,0.03707,0.03414,0.0098,0.0053,0.9997 6.500,0.6381,0.04031,0.03759,0.0125,0.0053,1.0000 6.750,0.6442,0.04362,0.04108,0.0154,0.0053,1.0000 7.000,0.6497,0.04713,0.04477,0.0178,0.0053,1.0000 7.250,0.6549,0.05091,0.04872,0.0196,0.0053,1.0000 7.500,0.6589,0.05490,0.05286,0.0209,0.0053,1.0000 7.750,0.6612,0.05906,0.05717,0.0217,0.0052,1.0000 8.000,0.6613,0.06339,0.06162,0.0219,0.0052,1.0000 8.250,0.6589,0.06788,0.06621,0.0215,0.0052,1.0000 8.500,0.6509,0.07222,0.07062,0.0208,0.0052,1.0000 8.750,0.6418,0.07738,0.07585,0.0175,0.0052,1.0000