Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ht08-il-100000-n5 Airfoil,ht08-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,26.0842 Max Cl/Cd alpha,4.5 Url,http://www.airfoiltools.com/polar/csv?polar=xf-ht08-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.750,-0.7415,0.09735,0.09251,0.0306,1.0000,0.0270 -8.500,-0.7433,0.09212,0.08732,0.0271,1.0000,0.0271 -8.250,-0.7462,0.08646,0.08172,0.0224,1.0000,0.0270 -8.000,-0.7454,0.07968,0.07493,0.0157,1.0000,0.0268 -7.750,-0.7423,0.07218,0.06736,0.0089,1.0000,0.0266 -7.500,-0.7373,0.06428,0.05929,0.0031,1.0000,0.0264 -7.250,-0.7300,0.05651,0.05123,-0.0012,1.0000,0.0262 -7.000,-0.7200,0.04898,0.04325,-0.0041,1.0000,0.0259 -6.750,-0.7060,0.04253,0.03621,-0.0057,1.0000,0.0258 -6.500,-0.6879,0.03733,0.03039,-0.0064,1.0000,0.0262 -6.250,-0.6669,0.03313,0.02556,-0.0066,1.0000,0.0269 -6.000,-0.6435,0.02987,0.02172,-0.0064,1.0000,0.0285 -5.750,-0.6182,0.02743,0.01861,-0.0061,1.0000,0.0313 -5.500,-0.5931,0.02476,0.01552,-0.0058,1.0000,0.0328 -5.250,-0.5677,0.02284,0.01343,-0.0055,1.0000,0.0349 -5.000,-0.5416,0.02142,0.01182,-0.0051,1.0000,0.0383 -4.750,-0.5148,0.02028,0.01039,-0.0047,1.0000,0.0431 -4.500,-0.4895,0.01876,0.00885,-0.0043,1.0000,0.0474 -4.250,-0.4631,0.01780,0.00775,-0.0039,1.0000,0.0545 -4.000,-0.4370,0.01683,0.00679,-0.0037,1.0000,0.0644 -3.750,-0.4106,0.01594,0.00588,-0.0034,1.0000,0.0779 -3.500,-0.3842,0.01512,0.00516,-0.0032,1.0000,0.1014 -3.250,-0.3579,0.01434,0.00452,-0.0030,1.0000,0.1407 -3.000,-0.3317,0.01360,0.00405,-0.0028,1.0000,0.2024 -2.750,-0.3058,0.01288,0.00369,-0.0026,1.0000,0.2877 -2.500,-0.2804,0.01214,0.00339,-0.0023,1.0000,0.3949 -2.250,-0.2565,0.01134,0.00314,-0.0014,1.0000,0.5335 -2.000,-0.2360,0.01054,0.00302,0.0009,1.0000,0.7051 -1.750,-0.2068,0.01003,0.00294,0.0023,1.0000,0.8919 -1.500,-0.1559,0.00986,0.00266,-0.0022,1.0000,1.0000 -1.250,-0.1301,0.00981,0.00247,-0.0018,1.0000,1.0000 -1.000,-0.1042,0.00976,0.00232,-0.0014,1.0000,1.0000 -0.750,-0.0782,0.00973,0.00220,-0.0011,1.0000,1.0000 -0.500,-0.0522,0.00970,0.00213,-0.0007,1.0000,1.0000 -0.250,-0.0261,0.00969,0.00207,-0.0004,1.0000,1.0000 0.000,0.0001,0.00968,0.00205,0.0000,1.0000,1.0000 0.250,0.0262,0.00969,0.00207,0.0004,1.0000,1.0000 0.500,0.0523,0.00970,0.00213,0.0007,1.0000,1.0000 0.750,0.0784,0.00973,0.00220,0.0011,1.0000,1.0000 1.000,0.1044,0.00976,0.00232,0.0014,1.0000,1.0000 1.250,0.1302,0.00981,0.00247,0.0018,1.0000,1.0000 1.500,0.1560,0.00986,0.00268,0.0022,1.0000,1.0000 1.750,0.2070,0.01003,0.00294,-0.0023,0.8911,1.0000 2.000,0.2361,0.01054,0.00302,-0.0009,0.7044,1.0000 2.250,0.2566,0.01134,0.00314,0.0014,0.5329,1.0000 2.500,0.2805,0.01214,0.00339,0.0023,0.3944,1.0000 2.750,0.3060,0.01288,0.00369,0.0026,0.2873,1.0000 3.000,0.3318,0.01361,0.00406,0.0028,0.2021,1.0000 3.250,0.3580,0.01435,0.00452,0.0030,0.1404,1.0000 3.500,0.3844,0.01512,0.00516,0.0032,0.1013,1.0000 3.750,0.4108,0.01594,0.00588,0.0034,0.0778,1.0000 4.000,0.4372,0.01683,0.00679,0.0037,0.0644,1.0000 4.250,0.4632,0.01781,0.00776,0.0039,0.0545,1.0000 4.500,0.4896,0.01877,0.00886,0.0043,0.0473,1.0000 4.750,0.5150,0.02029,0.01039,0.0047,0.0431,1.0000 5.000,0.5418,0.02142,0.01182,0.0051,0.0382,1.0000 5.250,0.5679,0.02285,0.01344,0.0055,0.0349,1.0000 5.500,0.5932,0.02477,0.01554,0.0057,0.0328,1.0000 5.750,0.6184,0.02744,0.01862,0.0061,0.0312,1.0000 6.000,0.6437,0.02989,0.02173,0.0064,0.0285,1.0000 6.250,0.6671,0.03315,0.02559,0.0065,0.0269,1.0000 6.500,0.6881,0.03736,0.03042,0.0064,0.0262,1.0000 6.750,0.7062,0.04257,0.03626,0.0057,0.0258,1.0000 7.000,0.7202,0.04903,0.04330,0.0041,0.0259,1.0000 7.250,0.7302,0.05657,0.05129,0.0011,0.0262,1.0000 7.500,0.7375,0.06436,0.05937,-0.0032,0.0264,1.0000 7.750,0.7425,0.07226,0.06744,-0.0090,0.0266,1.0000 8.000,0.7457,0.07976,0.07502,-0.0158,0.0268,1.0000 8.250,0.7466,0.08653,0.08179,-0.0226,0.0270,1.0000 8.500,0.7438,0.09219,0.08740,-0.0272,0.0271,1.0000 8.750,0.7420,0.09742,0.09258,-0.0308,0.0270,1.0000