Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-n64008a-il-500000 Airfoil,n64008a-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,46.548 Max Cl/Cd alpha,2.5 Url,http://www.airfoiltools.com/polar/csv?polar=xf-n64008a-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.6837,0.08251,0.08034,-0.0050,1.0000,0.0157 -9.000,-0.6934,0.07649,0.07425,-0.0102,1.0000,0.0157 -8.750,-0.7046,0.07182,0.06948,-0.0125,1.0000,0.0157 -8.500,-0.7112,0.06726,0.06480,-0.0135,1.0000,0.0157 -8.000,-0.7390,0.05230,0.04940,-0.0148,1.0000,0.0164 -7.750,-0.7343,0.04821,0.04514,-0.0146,1.0000,0.0169 -7.500,-0.7238,0.04512,0.04192,-0.0142,1.0000,0.0173 -7.250,-0.7115,0.04213,0.03874,-0.0137,1.0000,0.0179 -7.000,-0.6975,0.03914,0.03554,-0.0129,1.0000,0.0187 -6.750,-0.6819,0.03615,0.03231,-0.0120,1.0000,0.0198 -6.000,-0.6309,0.02254,0.01708,-0.0054,1.0000,0.0163 -5.750,-0.6103,0.01969,0.01391,-0.0042,1.0000,0.0166 -5.500,-0.5884,0.01800,0.01211,-0.0034,1.0000,0.0179 -5.250,-0.5653,0.01616,0.01008,-0.0022,1.0000,0.0181 -5.000,-0.5423,0.01487,0.00866,-0.0012,1.0000,0.0188 -4.750,-0.5196,0.01386,0.00756,-0.0001,1.0000,0.0197 -4.500,-0.4973,0.01296,0.00660,0.0010,1.0000,0.0206 -4.250,-0.4748,0.01234,0.00594,0.0020,1.0000,0.0221 -4.000,-0.4526,0.01171,0.00526,0.0031,1.0000,0.0234 -3.750,-0.4304,0.01119,0.00468,0.0042,1.0000,0.0242 -3.500,-0.4104,0.01019,0.00357,0.0056,1.0000,0.0269 -3.250,-0.3881,0.00975,0.00310,0.0065,1.0000,0.0307 -3.000,-0.3649,0.00939,0.00271,0.0073,0.9999,0.0381 -2.750,-0.3311,0.00803,0.00213,0.0051,0.9961,0.2172 -2.500,-0.3007,0.00647,0.00180,0.0033,0.9917,0.5312 -2.250,-0.2660,0.00606,0.00171,0.0016,0.9861,0.6290 -2.000,-0.2300,0.00580,0.00170,-0.0002,0.9817,0.7003 -1.750,-0.1971,0.00566,0.00166,-0.0013,0.9736,0.7367 -1.500,-0.1650,0.00553,0.00167,-0.0020,0.9658,0.7831 -1.250,-0.1344,0.00544,0.00166,-0.0023,0.9561,0.8138 -1.000,-0.1058,0.00537,0.00163,-0.0022,0.9441,0.8329 -0.750,-0.0782,0.00532,0.00160,-0.0019,0.9314,0.8484 -0.500,-0.0516,0.00528,0.00156,-0.0014,0.9178,0.8621 -0.250,-0.0257,0.00525,0.00154,-0.0007,0.9038,0.8759 0.000,0.0000,0.00525,0.00153,0.0000,0.8899,0.8898 0.250,0.0257,0.00525,0.00154,0.0007,0.8759,0.9038 0.500,0.0516,0.00528,0.00156,0.0014,0.8621,0.9178 0.750,0.0782,0.00532,0.00160,0.0019,0.8484,0.9313 1.000,0.1058,0.00537,0.00163,0.0022,0.8329,0.9441 1.250,0.1344,0.00544,0.00166,0.0023,0.8138,0.9561 1.500,0.1650,0.00553,0.00167,0.0020,0.7830,0.9657 1.750,0.1971,0.00566,0.00166,0.0013,0.7368,0.9735 2.000,0.2300,0.00580,0.00170,0.0002,0.7002,0.9816 2.250,0.2660,0.00606,0.00171,-0.0016,0.6289,0.9861 2.500,0.3007,0.00646,0.00180,-0.0033,0.5316,0.9916 2.750,0.3310,0.00802,0.00213,-0.0051,0.2174,0.9961 3.000,0.3648,0.00939,0.00271,-0.0073,0.0381,0.9999 3.250,0.3880,0.00974,0.00310,-0.0065,0.0307,1.0000 3.500,0.4103,0.01019,0.00357,-0.0056,0.0269,1.0000 3.750,0.4302,0.01119,0.00468,-0.0041,0.0242,1.0000 4.000,0.4525,0.01171,0.00526,-0.0030,0.0234,1.0000 4.250,0.4746,0.01234,0.00594,-0.0019,0.0222,1.0000 4.500,0.4972,0.01297,0.00661,-0.0009,0.0206,1.0000 4.750,0.5195,0.01385,0.00756,0.0002,0.0197,1.0000 5.000,0.5422,0.01487,0.00866,0.0012,0.0188,1.0000 5.250,0.5652,0.01616,0.01008,0.0023,0.0181,1.0000 5.500,0.5884,0.01803,0.01214,0.0034,0.0180,1.0000 5.750,0.6101,0.01974,0.01397,0.0042,0.0165,1.0000 6.000,0.6309,0.02254,0.01708,0.0054,0.0163,1.0000 11.750,0.5441,0.12552,0.12335,-0.0100,0.0156,1.0000 12.000,0.5437,0.12950,0.12733,-0.0115,0.0156,1.0000