Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca64208-il-100000 Airfoil,naca64208-il Reynolds number,100000 Ncrit,9 Mach,0 Max Cl/Cd,45.3063 Max Cl/Cd alpha,3.75 Url,http://airfoiltools.com/polar/csv?polar=xf-naca64208-il-100000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.5514,0.09410,0.08926,-0.0148,1.0000,0.0933 -8.500,-0.5698,0.08979,0.08508,-0.0225,1.0000,0.0949 -8.250,-0.5887,0.08553,0.08078,-0.0300,1.0000,0.0954 -8.000,-0.5543,0.08197,0.07731,-0.0203,1.0000,0.1030 -7.750,-0.5638,0.07713,0.07251,-0.0265,1.0000,0.1067 -7.500,-0.5888,0.07390,0.06886,-0.0357,1.0000,0.1094 -7.250,-0.5097,0.05761,0.05330,-0.0309,1.0000,0.1257 -7.000,-0.5056,0.05384,0.04951,-0.0311,1.0000,0.1340 -6.750,-0.5525,0.06099,0.05619,-0.0336,1.0000,0.1331 -6.500,-0.5450,0.05725,0.05240,-0.0340,1.0000,0.1435 -6.250,-0.5363,0.05391,0.04896,-0.0342,1.0000,0.1580 -6.000,-0.5286,0.05089,0.04588,-0.0339,1.0000,0.1822 -5.750,-0.5186,0.04843,0.04347,-0.0323,1.0000,0.2104 -5.000,-0.4394,0.03159,0.02388,-0.0353,1.0000,0.0841 -4.750,-0.4141,0.02831,0.01988,-0.0336,1.0000,0.0700 -4.500,-0.3910,0.02613,0.01740,-0.0323,1.0000,0.0671 -4.250,-0.3682,0.02447,0.01535,-0.0310,1.0000,0.0682 -4.000,-0.3463,0.02201,0.01276,-0.0300,1.0000,0.0711 -3.750,-0.3235,0.02036,0.01099,-0.0287,1.0000,0.0720 -3.500,-0.3014,0.01899,0.00954,-0.0273,1.0000,0.0748 -3.250,-0.2798,0.01792,0.00842,-0.0260,1.0000,0.0801 -3.000,-0.2594,0.01679,0.00743,-0.0248,1.0000,0.0910 -2.750,-0.2386,0.01578,0.00647,-0.0237,1.0000,0.1032 -2.500,-0.2165,0.01462,0.00554,-0.0231,1.0000,0.1460 -2.250,-0.2154,0.01212,0.00584,-0.0166,1.0000,0.7530 -2.000,-0.2138,0.01229,0.00612,-0.0097,1.0000,0.8352 -1.750,-0.2138,0.01237,0.00627,-0.0026,1.0000,0.8997 -1.500,-0.0751,0.01282,0.00622,-0.0192,1.0000,0.9971 -1.250,-0.0864,0.01258,0.00596,-0.0150,1.0000,1.0000 -1.000,-0.1013,0.01234,0.00566,-0.0101,1.0000,1.0000 -0.750,-0.0884,0.01235,0.00553,-0.0094,1.0000,1.0000 -0.500,-0.0685,0.01250,0.00553,-0.0096,1.0000,1.0000 -0.250,-0.0270,0.01286,0.00575,-0.0136,0.9934,1.0000 0.000,0.0187,0.01323,0.00601,-0.0182,0.9845,1.0000 0.250,0.0618,0.01357,0.00625,-0.0223,0.9752,1.0000 0.500,0.1071,0.01392,0.00655,-0.0266,0.9670,1.0000 0.750,0.1491,0.01422,0.00683,-0.0302,0.9576,1.0000 1.000,0.1888,0.01450,0.00712,-0.0332,0.9476,1.0000 1.250,0.2340,0.01478,0.00743,-0.0372,0.9399,1.0000 1.500,0.2731,0.01502,0.00773,-0.0400,0.9299,1.0000 1.750,0.3110,0.01527,0.00808,-0.0425,0.9199,1.0000 2.000,0.3599,0.01541,0.00836,-0.0468,0.9127,1.0000 2.250,0.3978,0.01556,0.00864,-0.0488,0.9012,1.0000 2.500,0.4336,0.01569,0.00893,-0.0503,0.8891,1.0000 2.750,0.4695,0.01575,0.00921,-0.0515,0.8762,1.0000 3.000,0.5122,0.01449,0.00812,-0.0501,0.8428,1.0000 3.250,0.5314,0.01322,0.00680,-0.0436,0.7875,1.0000 3.500,0.5518,0.01288,0.00654,-0.0402,0.7440,1.0000 3.750,0.5695,0.01257,0.00613,-0.0358,0.6611,1.0000 4.000,0.5627,0.01584,0.00646,-0.0288,0.1424,1.0000 4.250,0.5808,0.01759,0.00786,-0.0273,0.0992,1.0000 4.500,0.6011,0.01907,0.00923,-0.0259,0.0839,1.0000 4.750,0.6250,0.02046,0.01064,-0.0249,0.0764,1.0000 5.000,0.6504,0.02254,0.01257,-0.0243,0.0706,1.0000 5.250,0.6775,0.02394,0.01420,-0.0237,0.0647,1.0000 5.500,0.7056,0.02606,0.01648,-0.0231,0.0629,1.0000 5.750,0.7333,0.02855,0.01930,-0.0223,0.0630,1.0000 6.000,0.7598,0.03164,0.02291,-0.0212,0.0656,1.0000 6.250,0.7834,0.03476,0.02650,-0.0201,0.0664,1.0000 6.500,0.8049,0.03830,0.03050,-0.0189,0.0677,1.0000 10.750,0.6923,0.12340,0.11921,-0.0312,0.1113,1.0000 11.000,0.6655,0.12821,0.12396,-0.0373,0.1101,1.0000 11.250,0.6525,0.13234,0.12806,-0.0410,0.1055,1.0000