Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca16006-il-500000 Airfoil,naca16006-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,41.2344 Max Cl/Cd alpha,1.5 Url,http://airfoiltools.com/polar/csv?polar=xf-naca16006-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.5229,0.08508,0.08289,-0.0131,1.0000,0.0126 -8.750,-0.5268,0.08032,0.07814,-0.0151,1.0000,0.0127 -8.500,-0.5327,0.07530,0.07314,-0.0179,1.0000,0.0127 -8.250,-0.5430,0.06995,0.06779,-0.0222,1.0000,0.0127 -8.000,-0.5547,0.06558,0.06339,-0.0236,1.0000,0.0126 -7.750,-0.5646,0.06158,0.05934,-0.0233,1.0000,0.0127 -7.500,-0.5696,0.05726,0.05496,-0.0230,1.0000,0.0127 -7.250,-0.5726,0.05305,0.05066,-0.0220,1.0000,0.0127 -7.000,-0.5744,0.04895,0.04645,-0.0204,1.0000,0.0127 -6.750,-0.5745,0.04499,0.04238,-0.0185,1.0000,0.0128 -6.500,-0.5737,0.04109,0.03834,-0.0161,1.0000,0.0128 -6.250,-0.5719,0.03734,0.03444,-0.0135,1.0000,0.0128 -6.000,-0.5688,0.03379,0.03072,-0.0106,1.0000,0.0128 -5.750,-0.5648,0.03037,0.02711,-0.0076,1.0000,0.0129 -5.500,-0.5596,0.02706,0.02358,-0.0045,1.0000,0.0129 -5.250,-0.5684,0.01976,0.01585,0.0001,1.0000,0.0136 -5.000,-0.5617,0.01643,0.01227,0.0029,1.0000,0.0144 -4.750,-0.5493,0.01438,0.01005,0.0051,1.0000,0.0153 -4.500,-0.5345,0.01275,0.00825,0.0071,1.0000,0.0172 -4.250,-0.5097,0.01451,0.00988,0.0088,1.0000,0.0230 -3.500,-0.4567,0.01478,0.00851,0.0152,1.0000,0.0142 -3.250,-0.4319,0.01337,0.00691,0.0162,1.0000,0.0139 -3.000,-0.4082,0.01182,0.00525,0.0172,1.0000,0.0153 -2.750,-0.3844,0.01119,0.00458,0.0180,1.0000,0.0180 -2.500,-0.3603,0.01080,0.00414,0.0187,1.0000,0.0213 -2.250,-0.3362,0.01019,0.00344,0.0194,1.0000,0.0253 -2.000,-0.3117,0.00972,0.00293,0.0200,1.0000,0.0356 -1.750,-0.2870,0.00929,0.00255,0.0205,1.0000,0.0592 -1.500,-0.2642,0.00644,0.00217,0.0200,1.0000,0.7026 -1.250,-0.2461,0.00602,0.00254,0.0232,1.0000,0.9237 -1.000,-0.2158,0.00623,0.00273,0.0231,1.0000,0.9625 -0.750,-0.1513,0.00658,0.00301,0.0154,1.0000,0.9859 -0.250,-0.0074,0.00684,0.00316,-0.0037,1.0000,1.0000 0.000,0.0000,0.00684,0.00315,0.0000,1.0000,1.0000 0.250,0.0074,0.00684,0.00316,0.0037,1.0000,1.0000 0.750,0.1492,0.00659,0.00301,-0.0150,0.9862,1.0000 1.000,0.2156,0.00623,0.00273,-0.0230,0.9625,1.0000 1.250,0.2458,0.00602,0.00253,-0.0232,0.9242,1.0000 1.500,0.2639,0.00640,0.00217,-0.0200,0.7106,1.0000 1.750,0.2867,0.00929,0.00255,-0.0204,0.0593,1.0000 2.000,0.3113,0.00972,0.00292,-0.0199,0.0356,1.0000 2.250,0.3359,0.01017,0.00342,-0.0193,0.0254,1.0000 2.500,0.3600,0.01079,0.00413,-0.0186,0.0213,1.0000 2.750,0.3840,0.01119,0.00457,-0.0179,0.0180,1.0000 3.000,0.4078,0.01181,0.00524,-0.0171,0.0153,1.0000 3.250,0.4315,0.01337,0.00691,-0.0161,0.0138,1.0000 3.500,0.4562,0.01476,0.00850,-0.0151,0.0142,1.0000 4.250,0.5259,0.02324,0.01815,-0.0094,0.0205,1.0000 4.500,0.5456,0.02476,0.01991,-0.0074,0.0175,1.0000 4.750,0.5623,0.02639,0.02172,-0.0055,0.0154,1.0000 5.000,0.5765,0.02853,0.02402,-0.0035,0.0143,1.0000 5.250,0.5847,0.03240,0.02818,-0.0006,0.0135,1.0000 5.500,0.5815,0.03947,0.03569,0.0038,0.0129,1.0000 5.750,0.5900,0.04274,0.03920,0.0067,0.0128,1.0000 6.000,0.5976,0.04608,0.04275,0.0095,0.0128,1.0000 6.250,0.6046,0.04950,0.04635,0.0121,0.0128,1.0000 6.500,0.6112,0.05300,0.05002,0.0144,0.0128,1.0000 6.750,0.6174,0.05659,0.05377,0.0163,0.0127,1.0000 7.000,0.6231,0.06026,0.05757,0.0177,0.0127,1.0000 7.250,0.6290,0.06399,0.06142,0.0186,0.0126,1.0000 7.500,0.6357,0.06774,0.06532,0.0187,0.0124,1.0000 7.750,0.6442,0.07148,0.06915,0.0178,0.0120,1.0000 8.000,0.6486,0.07591,0.07365,0.0158,0.0116,1.0000 8.250,0.6477,0.08052,0.07831,0.0132,0.0114,1.0000 8.500,0.6420,0.08529,0.08309,0.0094,0.0114,1.0000