Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-usa5-il-200000 Airfoil,usa5-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,72.3724 Max Cl/Cd alpha,5.75 Url,http://airfoiltools.com/polar/csv?polar=xf-usa5-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -6.250,-0.3575,0.08076,0.07779,-0.0179,1.0000,0.0327 -6.000,-0.3582,0.07847,0.07553,-0.0173,1.0000,0.0338 -5.750,-0.3576,0.07612,0.07320,-0.0171,1.0000,0.0347 -5.500,-0.3553,0.07367,0.07077,-0.0172,1.0000,0.0357 -5.250,-0.3507,0.07104,0.06813,-0.0177,1.0000,0.0371 -5.000,-0.3414,0.06840,0.06547,-0.0194,1.0000,0.0389 -4.750,-0.2736,0.06393,0.06067,-0.0347,0.9940,0.0408 -4.500,-0.2501,0.05686,0.05358,-0.0390,0.9879,0.0420 -4.250,-0.2172,0.05294,0.04964,-0.0427,0.9832,0.0440 -4.000,-0.1823,0.04932,0.04590,-0.0470,0.9761,0.0476 -3.750,-0.1248,0.04419,0.04026,-0.0556,0.9705,0.0538 -3.500,-0.1002,0.04067,0.03680,-0.0572,0.9635,0.0564 -2.500,0.0493,0.02103,0.01498,-0.0644,0.9417,0.0403 -2.250,0.0764,0.01811,0.01153,-0.0639,0.9335,0.0431 -2.000,0.1171,0.01678,0.00994,-0.0660,0.9296,0.0497 -1.750,0.1547,0.01515,0.00799,-0.0673,0.9243,0.0566 -1.500,0.1908,0.01469,0.00748,-0.0685,0.9168,0.0703 -1.250,0.2255,0.01433,0.00705,-0.0695,0.9086,0.0865 -1.000,0.2618,0.01371,0.00629,-0.0706,0.9010,0.1052 -0.750,0.2912,0.01307,0.00570,-0.0706,0.8899,0.1257 -0.500,0.3217,0.01255,0.00516,-0.0708,0.8784,0.1411 -0.250,0.3519,0.01212,0.00472,-0.0708,0.8648,0.1552 0.000,0.3812,0.01175,0.00435,-0.0706,0.8485,0.1698 0.250,0.4105,0.01135,0.00390,-0.0704,0.8307,0.1800 0.500,0.4363,0.01108,0.00361,-0.0695,0.8082,0.1912 0.750,0.4626,0.01084,0.00333,-0.0688,0.7859,0.2034 1.000,0.4875,0.01062,0.00311,-0.0678,0.7622,0.2233 1.250,0.5988,0.00885,0.00285,-0.0864,0.7244,1.0000 1.500,0.6221,0.00903,0.00279,-0.0850,0.6900,1.0000 1.750,0.6445,0.00927,0.00278,-0.0836,0.6530,1.0000 2.000,0.6665,0.00956,0.00284,-0.0822,0.6155,1.0000 2.250,0.6884,0.00988,0.00292,-0.0808,0.5797,1.0000 2.500,0.7106,0.01018,0.00303,-0.0795,0.5460,1.0000 2.750,0.7332,0.01049,0.00316,-0.0784,0.5195,1.0000 3.000,0.7561,0.01080,0.00333,-0.0774,0.4985,1.0000 3.250,0.7794,0.01112,0.00355,-0.0765,0.4814,1.0000 3.500,0.8030,0.01143,0.00376,-0.0756,0.4673,1.0000 3.750,0.8268,0.01174,0.00400,-0.0748,0.4552,1.0000 4.000,0.8510,0.01202,0.00427,-0.0741,0.4441,1.0000 4.250,0.8751,0.01232,0.00456,-0.0734,0.4338,1.0000 4.500,0.8986,0.01262,0.00487,-0.0725,0.4212,1.0000 4.750,0.9192,0.01289,0.00505,-0.0711,0.3953,1.0000 5.000,0.9416,0.01314,0.00530,-0.0701,0.3775,1.0000 5.250,0.9640,0.01339,0.00555,-0.0691,0.3609,1.0000 5.500,0.9856,0.01364,0.00579,-0.0679,0.3377,1.0000 5.750,1.0067,0.01391,0.00606,-0.0666,0.3065,1.0000 6.000,1.0270,0.01430,0.00632,-0.0652,0.2570,1.0000 6.250,1.0414,0.01536,0.00685,-0.0631,0.1738,1.0000 6.500,1.0531,0.01687,0.00778,-0.0607,0.0796,1.0000 6.750,1.0642,0.01843,0.00901,-0.0579,0.0295,1.0000 7.000,1.0827,0.01922,0.00996,-0.0561,0.0267,1.0000 7.250,1.1006,0.02006,0.01102,-0.0542,0.0253,1.0000 7.500,1.1166,0.02103,0.01218,-0.0521,0.0244,1.0000 7.750,1.1300,0.02214,0.01348,-0.0496,0.0239,1.0000 8.000,1.1361,0.02377,0.01525,-0.0461,0.0225,1.0000 8.250,1.1418,0.02543,0.01699,-0.0426,0.0215,1.0000 8.500,1.1508,0.02694,0.01859,-0.0397,0.0214,1.0000 8.750,1.1612,0.02867,0.02038,-0.0370,0.0214,1.0000 9.000,1.1763,0.03082,0.02258,-0.0350,0.0215,1.0000 9.250,1.1987,0.03304,0.02486,-0.0341,0.0221,1.0000 9.500,1.2181,0.03418,0.02618,-0.0325,0.0229,1.0000 9.750,1.2423,0.03597,0.02835,-0.0309,0.0258,1.0000 10.000,1.2828,0.04198,0.03457,-0.0324,0.0315,1.0000