Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca0006-il-50000-n5 Airfoil,naca0006-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,22.8433 Max Cl/Cd alpha,3 Url,http://www.airfoiltools.com/polar/csv?polar=xf-naca0006-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.7042,0.09180,0.08516,0.0035,1.0000,0.0398 -8.500,-0.7055,0.08682,0.08020,0.0010,1.0000,0.0395 -8.250,-0.7061,0.08170,0.07504,-0.0017,1.0000,0.0392 -8.000,-0.7060,0.07655,0.06982,-0.0041,1.0000,0.0389 -7.750,-0.7048,0.07139,0.06454,-0.0063,1.0000,0.0386 -7.500,-0.7016,0.06624,0.05920,-0.0081,1.0000,0.0383 -7.250,-0.6960,0.06114,0.05384,-0.0095,1.0000,0.0380 -7.000,-0.6878,0.05610,0.04845,-0.0104,1.0000,0.0378 -6.750,-0.6766,0.05127,0.04318,-0.0108,1.0000,0.0378 -6.500,-0.6623,0.04669,0.03808,-0.0108,1.0000,0.0380 -6.250,-0.6451,0.04252,0.03320,-0.0104,1.0000,0.0393 -6.000,-0.6270,0.03891,0.02922,-0.0100,1.0000,0.0422 -5.750,-0.6057,0.03598,0.02593,-0.0095,1.0000,0.0452 -5.500,-0.5820,0.03284,0.02223,-0.0086,1.0000,0.0475 -5.250,-0.5569,0.03021,0.01896,-0.0078,1.0000,0.0528 -5.000,-0.5329,0.02801,0.01661,-0.0071,1.0000,0.0599 -4.750,-0.5072,0.02591,0.01423,-0.0061,1.0000,0.0680 -4.500,-0.4825,0.02429,0.01246,-0.0053,1.0000,0.0817 -4.250,-0.4574,0.02271,0.01069,-0.0043,1.0000,0.0938 -4.000,-0.4327,0.02137,0.00934,-0.0038,1.0000,0.1202 -3.750,-0.4087,0.01978,0.00791,-0.0033,1.0000,0.1583 -3.500,-0.3881,0.01792,0.00685,-0.0025,1.0000,0.2999 -3.250,-0.3731,0.01634,0.00646,0.0003,1.0000,0.5394 -3.000,-0.3543,0.01551,0.00658,0.0053,1.0000,0.7856 -2.750,-0.2956,0.01553,0.00629,0.0021,1.0000,0.9329 -2.500,-0.2247,0.01532,0.00551,-0.0062,1.0000,0.9906 -2.250,-0.1933,0.01503,0.00489,-0.0078,1.0000,1.0000 -2.000,-0.1723,0.01481,0.00445,-0.0071,1.0000,1.0000 -1.750,-0.1511,0.01464,0.00409,-0.0063,1.0000,1.0000 -1.500,-0.1297,0.01450,0.00379,-0.0055,1.0000,1.0000 -1.250,-0.1081,0.01439,0.00352,-0.0047,1.0000,1.0000 -1.000,-0.0866,0.01431,0.00332,-0.0038,1.0000,1.0000 -0.750,-0.0650,0.01424,0.00318,-0.0029,1.0000,1.0000 -0.500,-0.0434,0.01420,0.00307,-0.0019,1.0000,1.0000 -0.250,-0.0217,0.01417,0.00300,-0.0010,1.0000,1.0000 0.000,0.0000,0.01416,0.00298,0.0000,1.0000,1.0000 0.250,0.0217,0.01417,0.00300,0.0010,1.0000,1.0000 0.500,0.0434,0.01420,0.00307,0.0019,1.0000,1.0000 0.750,0.0650,0.01424,0.00317,0.0028,1.0000,1.0000 1.000,0.0866,0.01430,0.00332,0.0038,1.0000,1.0000 1.250,0.1082,0.01439,0.00352,0.0047,1.0000,1.0000 1.500,0.1297,0.01450,0.00379,0.0055,1.0000,1.0000 1.750,0.1512,0.01464,0.00409,0.0063,1.0000,1.0000 2.000,0.1724,0.01481,0.00445,0.0071,1.0000,1.0000 2.250,0.1934,0.01503,0.00488,0.0077,1.0000,1.0000 2.500,0.2247,0.01532,0.00551,0.0062,0.9907,1.0000 2.750,0.2956,0.01553,0.00629,-0.0021,0.9330,1.0000 3.000,0.3543,0.01551,0.00658,-0.0053,0.7856,1.0000 3.250,0.3731,0.01634,0.00646,-0.0003,0.5397,1.0000 3.500,0.3881,0.01792,0.00685,0.0025,0.3002,1.0000 3.750,0.4087,0.01978,0.00791,0.0033,0.1583,1.0000 4.000,0.4327,0.02137,0.00934,0.0038,0.1202,1.0000 4.250,0.4574,0.02271,0.01069,0.0043,0.0938,1.0000 4.500,0.4825,0.02429,0.01246,0.0053,0.0817,1.0000 4.750,0.5072,0.02591,0.01423,0.0061,0.0680,1.0000 5.000,0.5329,0.02801,0.01662,0.0071,0.0599,1.0000 5.250,0.5570,0.03022,0.01896,0.0077,0.0528,1.0000 5.500,0.5821,0.03284,0.02224,0.0086,0.0475,1.0000 5.750,0.6058,0.03598,0.02593,0.0095,0.0452,1.0000 6.000,0.6270,0.03891,0.02922,0.0100,0.0421,1.0000 6.250,0.6451,0.04252,0.03321,0.0104,0.0393,1.0000 6.500,0.6624,0.04670,0.03809,0.0108,0.0380,1.0000 6.750,0.6767,0.05128,0.04319,0.0108,0.0378,1.0000 7.000,0.6880,0.05611,0.04846,0.0103,0.0378,1.0000 7.250,0.6962,0.06115,0.05385,0.0094,0.0380,1.0000 7.500,0.7018,0.06626,0.05922,0.0081,0.0383,1.0000 7.750,0.7050,0.07141,0.06456,0.0063,0.0386,1.0000 8.000,0.7063,0.07658,0.06985,0.0041,0.0389,1.0000 8.250,0.7064,0.08173,0.07507,0.0016,0.0392,1.0000 8.500,0.7059,0.08685,0.08023,-0.0010,0.0395,1.0000 8.750,0.7046,0.09184,0.08520,-0.0036,0.0398,1.0000