Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca64a010-il-500000 Airfoil,naca64a010-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,50.7943 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-naca64a010-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.8014,0.02966,0.02488,-0.0120,1.0000,0.0171 -7.750,-0.7918,0.02643,0.02126,-0.0091,1.0000,0.0169 -7.500,-0.7774,0.02405,0.01859,-0.0069,1.0000,0.0171 -7.250,-0.7610,0.02199,0.01627,-0.0049,1.0000,0.0173 -7.000,-0.7422,0.02080,0.01489,-0.0032,1.0000,0.0179 -6.750,-0.7223,0.02047,0.01444,-0.0017,1.0000,0.0186 -6.500,-0.7052,0.01804,0.01179,0.0002,1.0000,0.0192 -6.250,-0.6885,0.01635,0.01002,0.0022,1.0000,0.0200 -6.000,-0.6715,0.01545,0.00907,0.0041,1.0000,0.0206 -5.750,-0.6545,0.01483,0.00843,0.0060,1.0000,0.0217 -5.500,-0.6384,0.01422,0.00778,0.0081,1.0000,0.0225 -5.250,-0.6174,0.01368,0.00719,0.0092,0.9993,0.0240 -5.000,-0.5806,0.01322,0.00669,0.0071,0.9961,0.0257 -4.750,-0.5488,0.01200,0.00537,0.0058,0.9917,0.0282 -4.500,-0.5133,0.01143,0.00479,0.0038,0.9877,0.0315 -4.250,-0.4781,0.01100,0.00431,0.0020,0.9832,0.0361 -4.000,-0.4433,0.01045,0.00375,0.0003,0.9784,0.0462 -3.750,-0.4101,0.00968,0.00321,-0.0012,0.9734,0.0917 -3.500,-0.3821,0.00827,0.00266,-0.0024,0.9668,0.2857 -3.250,-0.3581,0.00704,0.00232,-0.0024,0.9576,0.5037 -3.000,-0.3252,0.00668,0.00218,-0.0035,0.9512,0.5758 -2.750,-0.2961,0.00650,0.00208,-0.0038,0.9401,0.6145 -2.500,-0.2663,0.00636,0.00199,-0.0041,0.9292,0.6432 -2.250,-0.2378,0.00626,0.00192,-0.0041,0.9176,0.6700 -2.000,-0.2106,0.00619,0.00187,-0.0037,0.9055,0.6956 -1.750,-0.1848,0.00614,0.00186,-0.0030,0.8929,0.7233 -1.500,-0.1590,0.00612,0.00184,-0.0024,0.8800,0.7426 -1.250,-0.1328,0.00610,0.00181,-0.0019,0.8675,0.7568 -1.000,-0.1064,0.00608,0.00177,-0.0014,0.8555,0.7689 -0.750,-0.0798,0.00607,0.00174,-0.0011,0.8438,0.7796 -0.500,-0.0532,0.00608,0.00171,-0.0007,0.8327,0.7903 -0.250,-0.0265,0.00607,0.00169,-0.0004,0.8219,0.8001 0.000,0.0000,0.00606,0.00169,0.0000,0.8107,0.8107 0.250,0.0266,0.00607,0.00169,0.0004,0.8001,0.8219 0.500,0.0532,0.00608,0.00171,0.0007,0.7903,0.8328 0.750,0.0799,0.00607,0.00174,0.0011,0.7796,0.8438 1.000,0.1065,0.00608,0.00177,0.0014,0.7689,0.8555 1.250,0.1328,0.00610,0.00181,0.0019,0.7568,0.8675 1.500,0.1590,0.00612,0.00184,0.0024,0.7426,0.8800 1.750,0.1848,0.00614,0.00186,0.0030,0.7232,0.8928 2.000,0.2106,0.00619,0.00187,0.0037,0.6957,0.9054 2.250,0.2378,0.00626,0.00192,0.0041,0.6698,0.9176 2.500,0.2663,0.00636,0.00199,0.0041,0.6430,0.9292 2.750,0.2961,0.00650,0.00208,0.0038,0.6146,0.9402 3.000,0.3253,0.00668,0.00218,0.0035,0.5769,0.9511 3.250,0.3581,0.00705,0.00232,0.0024,0.5034,0.9576 3.500,0.3823,0.00824,0.00266,0.0023,0.2911,0.9667 3.750,0.4101,0.00968,0.00322,0.0012,0.0917,0.9734 4.000,0.4433,0.01045,0.00375,-0.0003,0.0463,0.9784 4.250,0.4779,0.01104,0.00436,-0.0020,0.0355,0.9833 4.500,0.5132,0.01144,0.00480,-0.0038,0.0317,0.9877 4.750,0.5487,0.01202,0.00539,-0.0057,0.0280,0.9916 5.000,0.5808,0.01319,0.00666,-0.0071,0.0256,0.9961 5.250,0.6174,0.01367,0.00719,-0.0092,0.0239,0.9993 5.500,0.6386,0.01420,0.00775,-0.0082,0.0225,1.0000 5.750,0.6547,0.01480,0.00839,-0.0061,0.0215,1.0000 6.000,0.6715,0.01548,0.00910,-0.0041,0.0207,1.0000 6.250,0.6885,0.01637,0.01003,-0.0021,0.0199,1.0000 6.500,0.7053,0.01800,0.01175,-0.0002,0.0192,1.0000 6.750,0.7223,0.02048,0.01445,0.0017,0.0186,1.0000 7.000,0.7419,0.02102,0.01513,0.0033,0.0180,1.0000 7.250,0.7608,0.02209,0.01637,0.0049,0.0173,1.0000 7.500,0.7773,0.02413,0.01867,0.0069,0.0171,1.0000 7.750,0.7917,0.02646,0.02130,0.0091,0.0170,1.0000 8.000,0.8011,0.02971,0.02494,0.0120,0.0172,1.0000 8.250,0.8038,0.03390,0.02953,0.0154,0.0178,1.0000 14.500,0.5143,0.14813,0.14595,-0.0098,0.0186,1.0000 14.750,0.5160,0.15146,0.14928,-0.0119,0.0185,1.0000