Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-raf26-il-500000 Airfoil,raf26-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,88.7606 Max Cl/Cd alpha,2 Url,http://airfoiltools.com/polar/csv?polar=xf-raf26-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.4104,0.08428,0.08210,-0.0218,1.0000,0.0169 -8.750,-0.4132,0.07987,0.07772,-0.0232,1.0000,0.0181 -8.500,-0.4156,0.07568,0.07354,-0.0244,1.0000,0.0184 -8.250,-0.4163,0.07194,0.06983,-0.0262,1.0000,0.0192 -8.000,-0.4205,0.06789,0.06580,-0.0272,1.0000,0.0193 -7.750,-0.4275,0.06389,0.06184,-0.0282,1.0000,0.0194 -7.500,-0.4392,0.06021,0.05820,-0.0288,1.0000,0.0194 -7.250,-0.4460,0.05537,0.05338,-0.0321,1.0000,0.0194 -7.000,-0.4491,0.04955,0.04751,-0.0361,1.0000,0.0194 -6.750,-0.4501,0.04390,0.04176,-0.0385,1.0000,0.0195 -6.500,-0.4496,0.03884,0.03656,-0.0395,1.0000,0.0195 -4.750,-0.3886,0.01735,0.01220,-0.0383,0.9956,0.0149 -4.500,-0.3571,0.01529,0.00979,-0.0390,0.9938,0.0155 -4.250,-0.3257,0.01397,0.00827,-0.0396,0.9912,0.0166 -4.000,-0.2931,0.01293,0.00705,-0.0406,0.9885,0.0178 -3.750,-0.2564,0.01278,0.00682,-0.0424,0.9858,0.0196 -3.500,-0.2246,0.01086,0.00473,-0.0433,0.9838,0.0226 -3.250,-0.1937,0.01029,0.00411,-0.0439,0.9790,0.0260 -3.000,-0.1601,0.00973,0.00348,-0.0451,0.9750,0.0330 -2.750,-0.1248,0.00918,0.00293,-0.0467,0.9722,0.0498 -2.500,-0.0949,0.00866,0.00261,-0.0473,0.9668,0.0992 -2.250,-0.0640,0.00806,0.00238,-0.0482,0.9621,0.1972 -2.000,-0.0311,0.00738,0.00222,-0.0497,0.9589,0.3482 -1.750,-0.0032,0.00696,0.00206,-0.0498,0.9514,0.4422 -1.500,0.0303,0.00647,0.00187,-0.0510,0.9462,0.5329 -1.250,0.0591,0.00598,0.00174,-0.0511,0.9376,0.6443 -1.000,0.0922,0.00528,0.00164,-0.0519,0.9315,0.8161 -0.750,0.1770,0.00519,0.00183,-0.0646,0.9365,1.0000 -0.500,0.2256,0.00508,0.00165,-0.0692,0.9281,1.0000 -0.250,0.2776,0.00497,0.00147,-0.0745,0.9164,1.0000 0.000,0.3264,0.00493,0.00131,-0.0791,0.8951,1.0000 0.250,0.3593,0.00499,0.00126,-0.0801,0.8731,1.0000 0.500,0.3860,0.00508,0.00126,-0.0797,0.8520,1.0000 0.750,0.4106,0.00516,0.00127,-0.0788,0.8309,1.0000 1.000,0.4346,0.00525,0.00128,-0.0778,0.8081,1.0000 1.250,0.4577,0.00535,0.00130,-0.0765,0.7815,1.0000 1.500,0.4802,0.00549,0.00132,-0.0752,0.7507,1.0000 1.750,0.5021,0.00566,0.00138,-0.0737,0.7155,1.0000 2.000,0.5228,0.00589,0.00144,-0.0720,0.6719,1.0000 2.250,0.5428,0.00619,0.00153,-0.0702,0.6199,1.0000 2.500,0.5615,0.00658,0.00164,-0.0681,0.5454,1.0000 2.750,0.5757,0.00735,0.00186,-0.0654,0.4212,1.0000 3.000,0.5933,0.00804,0.00212,-0.0634,0.3131,1.0000 3.250,0.6068,0.00920,0.00256,-0.0609,0.1491,1.0000 3.500,0.6270,0.00980,0.00287,-0.0595,0.0932,1.0000 3.750,0.6498,0.01015,0.00320,-0.0585,0.0838,1.0000 4.000,0.6734,0.01043,0.00352,-0.0576,0.0755,1.0000 4.250,0.6968,0.01073,0.00382,-0.0567,0.0651,1.0000 4.500,0.7195,0.01113,0.00406,-0.0556,0.0318,1.0000 4.750,0.7401,0.01181,0.00475,-0.0540,0.0222,1.0000 5.000,0.7619,0.01235,0.00536,-0.0527,0.0195,1.0000 5.250,0.7831,0.01297,0.00607,-0.0512,0.0176,1.0000 5.500,0.8034,0.01371,0.00687,-0.0497,0.0160,1.0000 5.750,0.8213,0.01486,0.00812,-0.0476,0.0147,1.0000 6.000,0.8364,0.01716,0.01064,-0.0450,0.0138,1.0000 6.250,0.8586,0.01812,0.01173,-0.0438,0.0132,1.0000 6.500,0.8812,0.01901,0.01275,-0.0427,0.0124,1.0000 6.750,0.9024,0.02064,0.01458,-0.0413,0.0120,1.0000 7.000,0.9226,0.02266,0.01686,-0.0396,0.0114,1.0000 7.250,0.9397,0.02564,0.02022,-0.0374,0.0114,1.0000 7.500,0.9495,0.03033,0.02546,-0.0340,0.0121,1.0000 7.750,0.9228,0.04616,0.04227,-0.0264,0.0213,1.0000 8.000,0.9000,0.03561,0.03228,-0.0203,0.0198,1.0000 8.250,0.9021,0.03949,0.03643,-0.0175,0.0187,1.0000 8.500,0.8978,0.04383,0.04099,-0.0148,0.0181,1.0000 8.750,0.8884,0.04822,0.04557,-0.0120,0.0176,1.0000 9.000,0.8729,0.05216,0.04966,-0.0088,0.0174,1.0000 9.250,0.8503,0.05578,0.05341,-0.0055,0.0174,1.0000 9.500,0.8243,0.06013,0.05787,-0.0043,0.0176,1.0000 9.750,0.7958,0.06575,0.06360,-0.0056,0.0180,1.0000 10.000,0.7668,0.07314,0.07107,-0.0096,0.0187,1.0000