Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-oa206-il-200000-n5 Airfoil,oa206-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,44.0931 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-oa206-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -6.750,-0.6406,0.05713,0.05327,-0.0005,1.0000,0.0156 -6.500,-0.6255,0.05201,0.04791,-0.0019,1.0000,0.0156 -6.250,-0.6115,0.05002,0.04590,-0.0027,1.0000,0.0168 -6.000,-0.5919,0.04738,0.04311,-0.0036,1.0000,0.0185 -5.750,-0.5709,0.04297,0.03840,-0.0044,1.0000,0.0190 -5.500,-0.5488,0.03768,0.03269,-0.0049,1.0000,0.0178 -5.250,-0.5247,0.03243,0.02690,-0.0049,1.0000,0.0170 -5.000,-0.4993,0.02822,0.02217,-0.0048,1.0000,0.0168 -4.750,-0.4729,0.02523,0.01874,-0.0047,1.0000,0.0171 -4.500,-0.4457,0.02285,0.01599,-0.0047,1.0000,0.0176 -4.250,-0.4180,0.02092,0.01374,-0.0047,1.0000,0.0185 -4.000,-0.3898,0.01963,0.01219,-0.0047,1.0000,0.0206 -3.750,-0.3615,0.01808,0.01035,-0.0046,1.0000,0.0215 -3.500,-0.3333,0.01672,0.00876,-0.0045,1.0000,0.0221 -3.250,-0.3054,0.01542,0.00733,-0.0044,1.0000,0.0229 -3.000,-0.2783,0.01411,0.00599,-0.0044,1.0000,0.0245 -2.750,-0.2506,0.01351,0.00541,-0.0046,1.0000,0.0274 -2.500,-0.2229,0.01291,0.00478,-0.0047,1.0000,0.0304 -2.250,-0.1953,0.01230,0.00410,-0.0047,1.0000,0.0324 -2.000,-0.1679,0.01161,0.00342,-0.0049,1.0000,0.0364 -1.750,-0.1406,0.01128,0.00308,-0.0050,1.0000,0.0437 -1.500,-0.1099,0.01087,0.00269,-0.0058,0.9917,0.0557 -1.250,-0.0745,0.01020,0.00236,-0.0077,0.9783,0.1400 -1.000,-0.0614,0.00772,0.00256,-0.0045,0.9648,0.8346 -0.750,-0.0450,0.00783,0.00274,-0.0005,0.9479,0.9221 -0.500,-0.0175,0.00782,0.00269,0.0009,0.9343,0.9720 -0.250,0.0416,0.00778,0.00256,-0.0053,0.9261,1.0000 0.000,0.0639,0.00777,0.00248,-0.0040,0.9102,1.0000 0.250,0.0859,0.00776,0.00240,-0.0027,0.8936,1.0000 0.500,0.1081,0.00774,0.00232,-0.0014,0.8752,1.0000 0.750,0.1305,0.00772,0.00224,0.0000,0.8537,1.0000 1.000,0.1528,0.00771,0.00216,0.0014,0.8282,1.0000 1.250,0.1752,0.00772,0.00207,0.0028,0.7969,1.0000 1.500,0.1984,0.00778,0.00199,0.0042,0.7581,1.0000 1.750,0.2223,0.00790,0.00195,0.0053,0.7103,1.0000 2.000,0.2473,0.00811,0.00192,0.0061,0.6496,1.0000 2.250,0.2731,0.00844,0.00193,0.0066,0.5744,1.0000 2.500,0.2998,0.00886,0.00200,0.0067,0.4928,1.0000 2.750,0.3271,0.00929,0.00214,0.0065,0.4275,1.0000 3.000,0.3549,0.00966,0.00235,0.0063,0.3825,1.0000 3.250,0.3828,0.00999,0.00256,0.0061,0.3480,1.0000 3.500,0.4108,0.01030,0.00279,0.0058,0.3167,1.0000 3.750,0.4388,0.01062,0.00303,0.0056,0.2859,1.0000 4.000,0.4667,0.01097,0.00332,0.0053,0.2490,1.0000 4.250,0.4944,0.01144,0.00359,0.0050,0.2001,1.0000 4.500,0.5219,0.01194,0.00392,0.0046,0.1571,1.0000 4.750,0.5494,0.01246,0.00430,0.0043,0.1197,1.0000 5.000,0.5766,0.01310,0.00479,0.0040,0.0764,1.0000 5.250,0.6036,0.01395,0.00545,0.0037,0.0423,1.0000 5.500,0.6307,0.01477,0.00626,0.0036,0.0301,1.0000 5.750,0.6579,0.01550,0.00713,0.0035,0.0256,1.0000 6.000,0.6842,0.01656,0.00828,0.0034,0.0219,1.0000 6.250,0.7106,0.01739,0.00927,0.0034,0.0193,1.0000 6.500,0.7366,0.01840,0.01041,0.0034,0.0175,1.0000 6.750,0.7619,0.01955,0.01168,0.0035,0.0162,1.0000 7.000,0.7864,0.02100,0.01324,0.0036,0.0152,1.0000 7.250,0.8088,0.02348,0.01591,0.0039,0.0144,1.0000 7.500,0.8337,0.02475,0.01750,0.0041,0.0136,1.0000 7.750,0.8577,0.02622,0.01926,0.0043,0.0123,1.0000 8.000,0.8799,0.02833,0.02172,0.0045,0.0117,1.0000 8.250,0.9002,0.03086,0.02463,0.0048,0.0112,1.0000 8.500,0.9181,0.03374,0.02793,0.0050,0.0108,1.0000 8.750,0.9329,0.03705,0.03168,0.0052,0.0105,1.0000 9.000,0.9434,0.04091,0.03599,0.0053,0.0104,1.0000 9.250,0.9479,0.04545,0.04099,0.0051,0.0103,1.0000 9.500,0.9441,0.05085,0.04684,0.0043,0.0102,1.0000 9.750,0.9294,0.05722,0.05359,0.0021,0.0103,1.0000 10.000,0.9015,0.06615,0.06281,-0.0053,0.0105,1.0000 10.250,0.8497,0.09147,0.08823,-0.0256,0.0114,1.0000