Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-oa206-il-50000 Airfoil,oa206-il Reynolds number,50000 Ncrit,9 Mach,0 Max Cl/Cd,27.318 Max Cl/Cd alpha,4 Url,http://www.airfoiltools.com/polar/csv?polar=xf-oa206-il-50000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.500,-0.6583,0.09753,0.09138,0.0351,1.0000,0.2665 -7.250,-0.6510,0.09372,0.08757,0.0364,1.0000,0.2897 -7.000,-0.6611,0.09096,0.08491,0.0336,1.0000,0.3116 -6.750,-0.6389,0.08688,0.08082,0.0398,1.0000,0.3469 -6.500,-0.6402,0.08408,0.07809,0.0408,1.0000,0.3819 -6.250,-0.6345,0.08121,0.07528,0.0445,1.0000,0.4254 -6.000,-0.5973,0.07726,0.07126,0.0529,1.0000,0.4915 -5.500,-0.5118,0.06990,0.06371,0.0670,1.0000,0.7065 -4.500,-0.4689,0.04065,0.03191,-0.0105,1.0000,0.1686 -4.250,-0.4378,0.03685,0.02756,-0.0111,1.0000,0.1507 -4.000,-0.4061,0.03393,0.02385,-0.0113,1.0000,0.1406 -3.750,-0.3760,0.03095,0.02043,-0.0112,1.0000,0.1333 -3.500,-0.3443,0.02884,0.01764,-0.0107,1.0000,0.1277 -3.250,-0.3148,0.02660,0.01510,-0.0102,1.0000,0.1270 -3.000,-0.2862,0.02457,0.01294,-0.0097,1.0000,0.1324 -2.750,-0.2574,0.02303,0.01123,-0.0090,1.0000,0.1416 -2.500,-0.2287,0.02137,0.00955,-0.0080,1.0000,0.1499 -2.250,-0.2021,0.02001,0.00819,-0.0069,1.0000,0.1674 -2.000,-0.1309,0.01495,0.00634,-0.0093,1.0000,1.0000 -1.750,-0.1068,0.01481,0.00557,-0.0084,1.0000,1.0000 -1.500,-0.0841,0.01469,0.00506,-0.0077,1.0000,1.0000 -1.250,-0.0619,0.01459,0.00471,-0.0069,1.0000,1.0000 -1.000,-0.0403,0.01451,0.00443,-0.0061,1.0000,1.0000 -0.750,-0.0193,0.01446,0.00422,-0.0052,1.0000,1.0000 -0.500,0.0010,0.01444,0.00407,-0.0041,1.0000,1.0000 -0.250,0.0208,0.01444,0.00395,-0.0030,1.0000,1.0000 0.000,0.0401,0.01446,0.00390,-0.0018,1.0000,1.0000 0.250,0.0590,0.01451,0.00389,-0.0005,1.0000,1.0000 0.500,0.0780,0.01459,0.00393,0.0007,1.0000,1.0000 0.750,0.0974,0.01469,0.00402,0.0017,1.0000,1.0000 1.000,0.1172,0.01483,0.00416,0.0026,1.0000,1.0000 1.250,0.1375,0.01500,0.00435,0.0034,1.0000,1.0000 1.500,0.1581,0.01521,0.00460,0.0040,1.0000,1.0000 1.750,0.1791,0.01546,0.00492,0.0045,1.0000,1.0000 2.000,0.2002,0.01577,0.00532,0.0047,1.0000,1.0000 2.250,0.2213,0.01614,0.00584,0.0048,1.0000,1.0000 2.500,0.2420,0.01661,0.00645,0.0046,1.0000,1.0000 2.750,0.2620,0.01723,0.00724,0.0041,1.0000,1.0000 3.000,0.3423,0.01820,0.00874,-0.0079,0.9654,1.0000 3.250,0.4470,0.01817,0.00945,-0.0190,0.8674,1.0000 3.500,0.4694,0.01786,0.00924,-0.0137,0.7830,1.0000 3.750,0.4831,0.01783,0.00903,-0.0073,0.6988,1.0000 4.000,0.4991,0.01827,0.00918,-0.0025,0.6149,1.0000 4.250,0.5186,0.01912,0.00963,0.0008,0.5380,1.0000 4.500,0.5402,0.02025,0.01042,0.0030,0.4684,1.0000 4.750,0.5631,0.02160,0.01154,0.0046,0.4023,1.0000 5.000,0.5853,0.02300,0.01270,0.0060,0.3338,1.0000 5.250,0.6067,0.02438,0.01374,0.0074,0.2570,1.0000 5.500,0.6295,0.02637,0.01535,0.0085,0.1873,1.0000 5.750,0.6552,0.02881,0.01788,0.0093,0.1503,1.0000 6.000,0.6805,0.03136,0.02052,0.0098,0.1294,1.0000 6.250,0.7059,0.03436,0.02369,0.0102,0.1178,1.0000 6.500,0.7309,0.03831,0.02851,0.0105,0.1130,1.0000 6.750,0.7532,0.04151,0.03175,0.0107,0.1050,1.0000 7.000,0.7723,0.04613,0.03725,0.0104,0.1028,1.0000 7.250,0.7891,0.05138,0.04301,0.0100,0.1038,1.0000 7.500,0.7951,0.05905,0.05166,0.0072,0.1102,1.0000 7.750,0.8014,0.06581,0.05875,0.0050,0.1158,1.0000 8.000,0.7949,0.07503,0.06837,-0.0011,0.1284,1.0000