Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ys900-il-200000 Airfoil,ys900-il Reynolds number,200000 Ncrit,9 Mach,0 Max Cl/Cd,21.4993 Max Cl/Cd alpha,3.5 Url,http://airfoiltools.com/polar/csv?polar=xf-ys900-il-200000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.500,-0.5098,0.09437,0.09130,-0.0244,1.0000,0.0287 -9.250,-0.5177,0.09005,0.08701,-0.0252,1.0000,0.0289 -9.000,-0.5280,0.08540,0.08239,-0.0263,1.0000,0.0291 -8.750,-0.5442,0.08000,0.07701,-0.0291,1.0000,0.0286 -8.500,-0.5669,0.07501,0.07199,-0.0307,1.0000,0.0278 -8.250,-0.5934,0.07124,0.06817,-0.0292,1.0000,0.0271 -8.000,-0.6226,0.06911,0.06595,-0.0245,1.0000,0.0265 -7.750,-0.6416,0.06650,0.06329,-0.0199,1.0000,0.0266 -7.500,-0.6523,0.06318,0.05994,-0.0165,1.0000,0.0271 -7.250,-0.7204,0.07422,0.07035,-0.0057,1.0000,0.0254 -7.000,-0.7331,0.06799,0.06408,-0.0026,1.0000,0.0261 -6.750,-0.7366,0.06386,0.05995,0.0001,1.0000,0.0270 -6.500,-0.7381,0.06077,0.05680,0.0033,1.0000,0.0279 -6.250,-0.7386,0.05782,0.05374,0.0067,1.0000,0.0291 -6.000,-0.7373,0.05500,0.05076,0.0102,1.0000,0.0305 -5.750,-0.7343,0.05216,0.04772,0.0138,1.0000,0.0323 -5.500,-0.7281,0.04968,0.04496,0.0177,1.0000,0.0350 -5.000,-0.7190,0.04401,0.03858,0.0263,1.0000,0.0394 -4.750,-0.7104,0.04096,0.03551,0.0286,1.0000,0.0419 -4.500,-0.6993,0.03891,0.03322,0.0317,1.0000,0.0467 -4.250,-0.6902,0.03660,0.03045,0.0357,1.0000,0.0527 -4.000,-0.6764,0.03429,0.02800,0.0378,1.0000,0.0586 -3.750,-0.6637,0.03214,0.02559,0.0405,1.0000,0.0686 -3.500,-0.6496,0.03030,0.02356,0.0428,1.0000,0.0826 -3.250,-0.6369,0.02849,0.02158,0.0452,1.0000,0.1069 -2.500,-0.5407,0.02238,0.01405,0.0512,1.0000,0.0353 -2.250,-0.5128,0.02160,0.01299,0.0529,1.0000,0.0253 -2.000,-0.4843,0.01925,0.01058,0.0532,1.0000,0.0220 -1.750,-0.4623,0.01800,0.00927,0.0549,1.0000,0.0196 -1.500,-0.0943,0.01853,0.01243,-0.0111,1.0000,1.0000 -1.250,-0.0788,0.01841,0.01226,-0.0092,1.0000,1.0000 -1.000,-0.0631,0.01831,0.01210,-0.0074,1.0000,1.0000 -0.750,-0.0474,0.01824,0.01198,-0.0055,1.0000,1.0000 -0.500,-0.0316,0.01819,0.01190,-0.0037,1.0000,1.0000 -0.250,-0.0158,0.01816,0.01185,-0.0019,1.0000,1.0000 0.000,0.0000,0.01815,0.01183,0.0000,1.0000,1.0000 0.250,0.0158,0.01816,0.01185,0.0018,1.0000,1.0000 0.500,0.0317,0.01819,0.01190,0.0036,1.0000,1.0000 0.750,0.0474,0.01825,0.01198,0.0055,1.0000,1.0000 1.000,0.0631,0.01832,0.01210,0.0073,1.0000,1.0000 1.250,0.0787,0.01841,0.01225,0.0092,1.0000,1.0000 1.500,0.0942,0.01853,0.01243,0.0110,1.0000,1.0000 1.750,0.1095,0.01868,0.01265,0.0129,1.0000,1.0000 3.500,0.6510,0.03028,0.02350,-0.0434,0.0856,1.0000 3.750,0.6650,0.03193,0.02538,-0.0409,0.0701,1.0000 4.000,0.6775,0.03444,0.02809,-0.0383,0.0605,1.0000 4.250,0.6919,0.03617,0.03005,-0.0359,0.0533,1.0000 4.500,0.7001,0.03907,0.03330,-0.0323,0.0481,1.0000 4.750,0.7123,0.04068,0.03523,-0.0290,0.0427,1.0000 5.000,0.7210,0.04356,0.03816,-0.0265,0.0398,1.0000 5.500,0.7272,0.05030,0.04546,-0.0185,0.0364,1.0000 5.750,0.7362,0.05192,0.04746,-0.0142,0.0328,1.0000 6.000,0.7395,0.05473,0.05048,-0.0106,0.0310,1.0000 6.250,0.7407,0.05760,0.05351,-0.0070,0.0294,1.0000 6.500,0.7404,0.06052,0.05656,-0.0035,0.0282,1.0000 6.750,0.7388,0.06353,0.05964,-0.0003,0.0273,1.0000 7.000,0.7355,0.06724,0.06337,0.0026,0.0264,1.0000 7.250,0.7260,0.07294,0.06908,0.0055,0.0256,1.0000 7.500,0.7119,0.07860,0.07480,0.0089,0.0252,1.0000 7.750,0.7036,0.08137,0.07769,0.0126,0.0252,1.0000 8.000,0.6931,0.08415,0.08058,0.0163,0.0251,1.0000 8.250,0.6818,0.08686,0.08338,0.0197,0.0251,1.0000 8.500,0.6653,0.08917,0.08574,0.0239,0.0251,1.0000 8.750,0.6480,0.09124,0.08785,0.0277,0.0251,1.0000 9.000,0.6313,0.09387,0.09051,0.0303,0.0251,1.0000 9.250,0.6169,0.09702,0.09370,0.0314,0.0251,1.0000