Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ht08-il-200000-n5 Airfoil,ht08-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,34.1925 Max Cl/Cd alpha,4.75 Url,http://www.airfoiltools.com/polar/csv?polar=xf-ht08-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.7631,0.09521,0.09179,0.0327,1.0000,0.0146 -8.750,-0.7667,0.08966,0.08627,0.0292,1.0000,0.0144 -8.500,-0.7715,0.08369,0.08035,0.0245,1.0000,0.0143 -8.250,-0.7733,0.07619,0.07285,0.0166,1.0000,0.0141 -8.000,-0.7720,0.06716,0.06372,0.0081,1.0000,0.0139 -7.750,-0.7697,0.05687,0.05320,0.0012,1.0000,0.0137 -7.500,-0.7669,0.04593,0.04177,-0.0033,1.0000,0.0136 -7.250,-0.7586,0.03699,0.03209,-0.0052,1.0000,0.0138 -7.000,-0.7426,0.03102,0.02534,-0.0055,1.0000,0.0142 -6.750,-0.7216,0.02714,0.02079,-0.0054,1.0000,0.0149 -6.500,-0.6985,0.02447,0.01760,-0.0052,1.0000,0.0161 -6.250,-0.6743,0.02280,0.01574,-0.0051,1.0000,0.0173 -6.000,-0.6491,0.02111,0.01377,-0.0048,1.0000,0.0182 -5.750,-0.6234,0.01957,0.01196,-0.0044,1.0000,0.0193 -5.500,-0.5973,0.01819,0.01033,-0.0041,1.0000,0.0207 -5.250,-0.5707,0.01733,0.00927,-0.0038,1.0000,0.0225 -5.000,-0.5451,0.01601,0.00790,-0.0036,1.0000,0.0252 -4.750,-0.5186,0.01516,0.00697,-0.0033,1.0000,0.0276 -4.500,-0.4918,0.01441,0.00611,-0.0030,1.0000,0.0306 -4.250,-0.4651,0.01367,0.00531,-0.0029,1.0000,0.0356 -4.000,-0.4379,0.01311,0.00467,-0.0027,1.0000,0.0413 -3.750,-0.4108,0.01252,0.00409,-0.0026,1.0000,0.0501 -3.500,-0.3836,0.01202,0.00361,-0.0025,1.0000,0.0642 -3.250,-0.3564,0.01154,0.00318,-0.0024,1.0000,0.0851 -3.000,-0.3293,0.01108,0.00286,-0.0023,1.0000,0.1193 -2.750,-0.3022,0.01062,0.00258,-0.0023,1.0000,0.1643 -2.500,-0.2752,0.01015,0.00235,-0.0023,1.0000,0.2229 -2.250,-0.2484,0.00968,0.00214,-0.0022,1.0000,0.2937 -2.000,-0.2218,0.00918,0.00198,-0.0021,1.0000,0.3788 -1.750,-0.1959,0.00863,0.00185,-0.0019,1.0000,0.4829 -1.500,-0.1715,0.00800,0.00176,-0.0011,1.0000,0.6135 -1.250,-0.1504,0.00740,0.00172,0.0009,1.0000,0.7585 -1.000,-0.1262,0.00705,0.00173,0.0028,1.0000,0.8983 -0.750,-0.0805,0.00693,0.00165,-0.0007,1.0000,0.9960 -0.500,-0.0529,0.00691,0.00159,-0.0006,1.0000,1.0000 -0.250,-0.0264,0.00690,0.00154,-0.0003,1.0000,1.0000 0.000,0.0001,0.00689,0.00153,0.0000,1.0000,1.0000 0.250,0.0266,0.00690,0.00154,0.0003,1.0000,1.0000 0.500,0.0530,0.00691,0.00159,0.0006,1.0000,1.0000 0.750,0.0808,0.00693,0.00165,0.0007,0.9957,1.0000 1.000,0.1264,0.00705,0.00173,-0.0028,0.8976,1.0000 1.250,0.1505,0.00740,0.00172,-0.0009,0.7581,1.0000 1.500,0.1716,0.00800,0.00176,0.0011,0.6126,1.0000 1.750,0.1960,0.00863,0.00185,0.0019,0.4824,1.0000 2.000,0.2219,0.00918,0.00198,0.0021,0.3785,1.0000 2.250,0.2485,0.00968,0.00214,0.0022,0.2934,1.0000 2.500,0.2753,0.01015,0.00235,0.0023,0.2225,1.0000 2.750,0.3023,0.01062,0.00258,0.0023,0.1639,1.0000 3.000,0.3294,0.01108,0.00286,0.0023,0.1191,1.0000 3.250,0.3565,0.01155,0.00319,0.0024,0.0850,1.0000 3.500,0.3838,0.01202,0.00362,0.0024,0.0641,1.0000 3.750,0.4110,0.01252,0.00409,0.0026,0.0501,1.0000 4.000,0.4381,0.01311,0.00468,0.0027,0.0413,1.0000 4.250,0.4652,0.01367,0.00531,0.0029,0.0356,1.0000 4.500,0.4919,0.01442,0.00611,0.0030,0.0305,1.0000 4.750,0.5187,0.01517,0.00697,0.0033,0.0275,1.0000 5.000,0.5453,0.01602,0.00790,0.0035,0.0252,1.0000 5.250,0.5709,0.01734,0.00928,0.0038,0.0225,1.0000 5.500,0.5975,0.01820,0.01034,0.0041,0.0206,1.0000 5.750,0.6236,0.01957,0.01197,0.0044,0.0193,1.0000 6.000,0.6493,0.02112,0.01378,0.0048,0.0181,1.0000 6.250,0.6745,0.02282,0.01576,0.0050,0.0173,1.0000 6.500,0.6987,0.02448,0.01761,0.0051,0.0162,1.0000 6.750,0.7218,0.02717,0.02082,0.0053,0.0149,1.0000 7.000,0.7428,0.03104,0.02536,0.0055,0.0142,1.0000 7.250,0.7588,0.03704,0.03214,0.0051,0.0138,1.0000 7.500,0.7671,0.04599,0.04183,0.0032,0.0136,1.0000 7.750,0.7700,0.05694,0.05327,-0.0012,0.0137,1.0000 8.000,0.7723,0.06723,0.06380,-0.0082,0.0139,1.0000 8.250,0.7736,0.07628,0.07294,-0.0167,0.0141,1.0000 8.500,0.7719,0.08377,0.08042,-0.0246,0.0143,1.0000 8.750,0.7671,0.08974,0.08635,-0.0293,0.0144,1.0000 9.000,0.7636,0.09531,0.09188,-0.0329,0.0146,1.0000