Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-n64008a-il-100000-n5 Airfoil,n64008a-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,30.1144 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-n64008a-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.250,-0.6864,0.08802,0.08323,-0.0019,1.0000,0.0258 -9.000,-0.6932,0.08152,0.07674,-0.0075,1.0000,0.0253 -8.750,-0.7030,0.07603,0.07121,-0.0113,1.0000,0.0250 -8.500,-0.7118,0.07109,0.06617,-0.0132,1.0000,0.0247 -8.250,-0.7166,0.06610,0.06103,-0.0146,1.0000,0.0244 -8.000,-0.7183,0.06118,0.05590,-0.0152,1.0000,0.0240 -7.750,-0.7166,0.05632,0.05077,-0.0153,1.0000,0.0236 -7.500,-0.7117,0.05158,0.04570,-0.0150,1.0000,0.0233 -7.250,-0.7035,0.04707,0.04080,-0.0142,1.0000,0.0231 -7.000,-0.6924,0.04284,0.03614,-0.0132,1.0000,0.0231 -6.750,-0.6784,0.03895,0.03176,-0.0119,1.0000,0.0233 -6.500,-0.6619,0.03545,0.02776,-0.0106,1.0000,0.0238 -6.250,-0.6424,0.03282,0.02460,-0.0094,1.0000,0.0261 -6.000,-0.6209,0.03057,0.02181,-0.0081,1.0000,0.0275 -5.750,-0.5984,0.02823,0.01903,-0.0070,1.0000,0.0280 -5.500,-0.5757,0.02542,0.01594,-0.0061,1.0000,0.0289 -5.250,-0.5524,0.02335,0.01373,-0.0054,1.0000,0.0304 -5.000,-0.5292,0.02205,0.01229,-0.0047,1.0000,0.0334 -4.750,-0.5055,0.02092,0.01102,-0.0038,1.0000,0.0372 -4.500,-0.4827,0.01966,0.00966,-0.0028,1.0000,0.0389 -4.250,-0.4614,0.01848,0.00841,-0.0015,1.0000,0.0409 -4.000,-0.4409,0.01743,0.00733,-0.0003,1.0000,0.0448 -3.750,-0.4190,0.01666,0.00644,0.0008,1.0000,0.0511 -3.500,-0.3976,0.01584,0.00562,0.0018,1.0000,0.0682 -3.250,-0.3781,0.01461,0.00482,0.0029,1.0000,0.1385 -3.000,-0.3685,0.01223,0.00439,0.0054,1.0000,0.5296 -2.750,-0.3505,0.01177,0.00442,0.0081,1.0000,0.6661 -2.500,-0.3348,0.01165,0.00467,0.0120,1.0000,0.7751 -2.250,-0.3176,0.01173,0.00488,0.0158,1.0000,0.8422 -2.000,-0.2934,0.01173,0.00477,0.0172,1.0000,0.8706 -1.750,-0.2660,0.01168,0.00461,0.0173,1.0000,0.8875 -1.500,-0.2370,0.01164,0.00447,0.0170,1.0000,0.9036 -1.250,-0.2061,0.01161,0.00435,0.0162,1.0000,0.9196 -1.000,-0.1731,0.01161,0.00424,0.0148,1.0000,0.9356 -0.750,-0.1379,0.01161,0.00418,0.0128,1.0000,0.9513 -0.500,-0.0955,0.01164,0.00414,0.0093,0.9962,0.9636 -0.250,-0.0479,0.01166,0.00411,0.0047,0.9888,0.9728 0.000,0.0000,0.01167,0.00411,0.0000,0.9811,0.9811 0.250,0.0479,0.01166,0.00411,-0.0047,0.9728,0.9888 0.500,0.0955,0.01164,0.00414,-0.0093,0.9636,0.9962 1.000,0.1731,0.01161,0.00424,-0.0148,0.9357,1.0000 1.250,0.2061,0.01161,0.00435,-0.0162,0.9196,1.0000 1.500,0.2370,0.01164,0.00447,-0.0170,0.9036,1.0000 1.750,0.2660,0.01168,0.00461,-0.0173,0.8875,1.0000 2.000,0.2935,0.01173,0.00477,-0.0172,0.8706,1.0000 2.250,0.3177,0.01173,0.00488,-0.0158,0.8422,1.0000 2.500,0.3349,0.01165,0.00467,-0.0120,0.7750,1.0000 2.750,0.3506,0.01177,0.00442,-0.0081,0.6659,1.0000 3.000,0.3686,0.01224,0.00439,-0.0054,0.5292,1.0000 3.250,0.3782,0.01461,0.00482,-0.0029,0.1382,1.0000 3.500,0.3977,0.01584,0.00562,-0.0018,0.0681,1.0000 3.750,0.4191,0.01666,0.00644,-0.0008,0.0510,1.0000 4.000,0.4410,0.01743,0.00733,0.0003,0.0448,1.0000 4.250,0.4615,0.01848,0.00841,0.0015,0.0409,1.0000 4.500,0.4827,0.01966,0.00966,0.0027,0.0389,1.0000 4.750,0.5056,0.02092,0.01102,0.0038,0.0372,1.0000 5.000,0.5292,0.02205,0.01229,0.0046,0.0334,1.0000 5.250,0.5525,0.02335,0.01373,0.0053,0.0304,1.0000 5.500,0.5757,0.02542,0.01594,0.0061,0.0289,1.0000 5.750,0.5984,0.02823,0.01903,0.0070,0.0280,1.0000 6.000,0.6209,0.03056,0.02181,0.0081,0.0275,1.0000 6.250,0.6423,0.03282,0.02460,0.0094,0.0261,1.0000 6.500,0.6619,0.03545,0.02776,0.0106,0.0238,1.0000 6.750,0.6784,0.03895,0.03176,0.0119,0.0233,1.0000 7.000,0.6923,0.04284,0.03613,0.0132,0.0231,1.0000 7.250,0.7035,0.04706,0.04079,0.0142,0.0231,1.0000 7.500,0.7116,0.05158,0.04569,0.0150,0.0233,1.0000 7.750,0.7165,0.05632,0.05076,0.0154,0.0236,1.0000 8.000,0.7182,0.06118,0.05590,0.0153,0.0240,1.0000 8.250,0.7167,0.06610,0.06103,0.0146,0.0244,1.0000 8.500,0.7119,0.07109,0.06617,0.0132,0.0246,1.0000 8.750,0.7032,0.07604,0.07121,0.0113,0.0250,1.0000 9.000,0.6934,0.08152,0.07674,0.0075,0.0253,1.0000 9.250,0.6867,0.08803,0.08324,0.0019,0.0258,1.0000