Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ht05-il-200000-n5 Airfoil,ht05-il Reynolds number,200000 Ncrit,5 Mach,0 Max Cl/Cd,34.5709 Max Cl/Cd alpha,4.75 Url,http://airfoiltools.com/polar/csv?polar=xf-ht05-il-200000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.7447,0.09428,0.09080,0.0260,1.0000,0.0150 -8.750,-0.7494,0.08864,0.08521,0.0224,1.0000,0.0149 -8.500,-0.7559,0.08258,0.07919,0.0176,1.0000,0.0147 -8.250,-0.7584,0.07508,0.07168,0.0108,1.0000,0.0145 -8.000,-0.7589,0.06510,0.06162,0.0019,1.0000,0.0143 -7.750,-0.7626,0.05111,0.04727,-0.0062,1.0000,0.0140 -7.500,-0.7640,0.03920,0.03459,-0.0092,1.0000,0.0140 -7.250,-0.7524,0.03315,0.02785,-0.0094,1.0000,0.0143 -7.000,-0.7352,0.02900,0.02309,-0.0089,1.0000,0.0150 -6.750,-0.7144,0.02615,0.01971,-0.0083,1.0000,0.0160 -6.500,-0.6911,0.02435,0.01746,-0.0077,1.0000,0.0173 -6.250,-0.6688,0.02180,0.01450,-0.0070,1.0000,0.0183 -6.000,-0.6450,0.02012,0.01261,-0.0064,1.0000,0.0193 -5.750,-0.6203,0.01892,0.01121,-0.0059,1.0000,0.0205 -5.500,-0.5953,0.01779,0.00991,-0.0053,1.0000,0.0221 -5.250,-0.5697,0.01699,0.00894,-0.0048,1.0000,0.0245 -5.000,-0.5447,0.01588,0.00772,-0.0042,1.0000,0.0269 -4.750,-0.5194,0.01503,0.00680,-0.0037,1.0000,0.0296 -4.500,-0.4937,0.01436,0.00602,-0.0032,1.0000,0.0330 -4.250,-0.4679,0.01372,0.00532,-0.0028,1.0000,0.0383 -4.000,-0.4420,0.01318,0.00475,-0.0023,1.0000,0.0449 -3.750,-0.4160,0.01264,0.00420,-0.0019,1.0000,0.0541 -3.500,-0.3900,0.01217,0.00375,-0.0015,1.0000,0.0689 -3.250,-0.3640,0.01175,0.00337,-0.0010,1.0000,0.0879 -3.000,-0.3381,0.01133,0.00308,-0.0007,1.0000,0.1176 -2.750,-0.3122,0.01096,0.00284,-0.0003,1.0000,0.1510 -2.500,-0.2863,0.01060,0.00263,0.0001,1.0000,0.1904 -2.250,-0.2605,0.01024,0.00243,0.0005,1.0000,0.2346 -2.000,-0.2350,0.00987,0.00227,0.0010,1.0000,0.2874 -1.750,-0.2098,0.00945,0.00214,0.0015,1.0000,0.3594 -1.500,-0.1854,0.00896,0.00209,0.0021,1.0000,0.4647 -1.250,-0.1610,0.00863,0.00208,0.0030,1.0000,0.5628 -1.000,-0.1350,0.00851,0.00202,0.0036,1.0000,0.6137 -0.750,-0.1095,0.00827,0.00188,0.0042,1.0000,0.6421 -0.500,-0.0878,0.00761,0.00181,0.0059,1.0000,0.7156 -0.250,-0.0330,0.00738,0.00203,0.0011,1.0000,0.9869 0.000,0.0001,0.00739,0.00203,0.0000,1.0000,1.0000 0.250,0.0332,0.00738,0.00203,-0.0011,0.9868,1.0000 0.500,0.0878,0.00762,0.00180,-0.0059,0.7120,1.0000 0.750,0.1096,0.00827,0.00188,-0.0042,0.6419,1.0000 1.000,0.1352,0.00851,0.00202,-0.0036,0.6135,1.0000 1.250,0.1611,0.00863,0.00208,-0.0030,0.5622,1.0000 1.500,0.1856,0.00896,0.00209,-0.0021,0.4640,1.0000 1.750,0.2099,0.00945,0.00214,-0.0015,0.3592,1.0000 2.000,0.2351,0.00987,0.00227,-0.0010,0.2874,1.0000 2.250,0.2607,0.01024,0.00243,-0.0005,0.2345,1.0000 2.500,0.2864,0.01060,0.00263,-0.0001,0.1900,1.0000 2.750,0.3123,0.01096,0.00284,0.0003,0.1508,1.0000 3.000,0.3382,0.01133,0.00308,0.0007,0.1175,1.0000 3.250,0.3641,0.01175,0.00337,0.0010,0.0879,1.0000 3.500,0.3902,0.01217,0.00375,0.0015,0.0688,1.0000 3.750,0.4162,0.01264,0.00421,0.0019,0.0539,1.0000 4.000,0.4421,0.01318,0.00475,0.0023,0.0449,1.0000 4.250,0.4681,0.01373,0.00533,0.0028,0.0382,1.0000 4.500,0.4938,0.01436,0.00602,0.0032,0.0329,1.0000 4.750,0.5196,0.01503,0.00680,0.0037,0.0295,1.0000 5.000,0.5448,0.01591,0.00774,0.0042,0.0269,1.0000 5.250,0.5699,0.01698,0.00894,0.0048,0.0245,1.0000 5.500,0.5954,0.01780,0.00992,0.0053,0.0221,1.0000 5.750,0.6205,0.01892,0.01121,0.0059,0.0205,1.0000 6.000,0.6452,0.02013,0.01261,0.0064,0.0193,1.0000 6.250,0.6688,0.02187,0.01457,0.0070,0.0183,1.0000 6.500,0.6913,0.02433,0.01745,0.0077,0.0173,1.0000 6.750,0.7146,0.02615,0.01971,0.0083,0.0159,1.0000 7.000,0.7353,0.02905,0.02314,0.0089,0.0150,1.0000 7.250,0.7525,0.03317,0.02788,0.0094,0.0144,1.0000 7.500,0.7643,0.03918,0.03457,0.0092,0.0140,1.0000 7.750,0.7628,0.05111,0.04727,0.0062,0.0140,1.0000 8.000,0.7590,0.06520,0.06172,-0.0020,0.0143,1.0000 8.250,0.7586,0.07519,0.07179,-0.0109,0.0146,1.0000 8.500,0.7561,0.08268,0.07929,-0.0178,0.0148,1.0000 8.750,0.7496,0.08876,0.08533,-0.0226,0.0149,1.0000 9.000,0.7451,0.09440,0.09092,-0.0262,0.0151,1.0000