Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-ah85l120-il-500000 Airfoil,ah85l120-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,48.3312 Max Cl/Cd alpha,3.75 Url,http://www.airfoiltools.com/polar/csv?polar=xf-ah85l120-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.500,-0.7020,0.02394,0.01822,-0.0433,0.9403,0.0147 -8.250,-0.6738,0.02111,0.01509,-0.0435,0.9382,0.0142 -8.000,-0.6556,0.02110,0.01506,-0.0425,0.9342,0.0156 -7.750,-0.6278,0.01951,0.01329,-0.0428,0.9320,0.0163 -7.500,-0.5995,0.01810,0.01175,-0.0432,0.9301,0.0164 -7.250,-0.5742,0.01698,0.01053,-0.0431,0.9280,0.0169 -7.000,-0.5544,0.01631,0.00978,-0.0419,0.9252,0.0179 -6.750,-0.5353,0.01573,0.00913,-0.0405,0.9220,0.0184 -6.500,-0.5161,0.01521,0.00855,-0.0391,0.9191,0.0191 -6.250,-0.5072,0.01398,0.00718,-0.0358,0.9159,0.0210 -6.000,-0.4904,0.01356,0.00675,-0.0340,0.9131,0.0231 -5.750,-0.4732,0.01317,0.00630,-0.0322,0.9101,0.0252 -5.500,-0.4546,0.01280,0.00588,-0.0305,0.9073,0.0281 -5.250,-0.4381,0.01227,0.00532,-0.0285,0.9045,0.0382 -5.000,-0.4243,0.01160,0.00490,-0.0261,0.9018,0.0872 -4.750,-0.4153,0.01080,0.00456,-0.0230,0.8987,0.1888 -4.500,-0.4083,0.00993,0.00424,-0.0195,0.8950,0.3110 -4.250,-0.4060,0.00896,0.00393,-0.0150,0.8913,0.4609 -4.000,-0.3995,0.00829,0.00374,-0.0108,0.8883,0.5797 -3.750,-0.3858,0.00796,0.00375,-0.0079,0.8856,0.6615 -3.500,-0.3654,0.00790,0.00383,-0.0063,0.8827,0.7083 -3.250,-0.3431,0.00800,0.00397,-0.0049,0.8799,0.7462 -3.000,-0.3193,0.00822,0.00420,-0.0038,0.8774,0.7716 -2.750,-0.2927,0.00838,0.00433,-0.0034,0.8753,0.7826 -2.500,-0.2663,0.00857,0.00448,-0.0029,0.8733,0.7921 -2.250,-0.2421,0.00871,0.00457,-0.0022,0.8703,0.8005 -2.000,-0.2148,0.00885,0.00471,-0.0020,0.8673,0.8064 -1.750,-0.1889,0.00901,0.00484,-0.0014,0.8644,0.8143 -1.500,-0.1607,0.00915,0.00497,-0.0013,0.8621,0.8199 -1.250,-0.1325,0.00933,0.00512,-0.0012,0.8602,0.8260 -1.000,-0.1077,0.00943,0.00520,-0.0006,0.8575,0.8318 -0.750,-0.0805,0.00949,0.00528,-0.0005,0.8541,0.8347 -0.500,-0.0533,0.00953,0.00532,-0.0004,0.8509,0.8382 -0.250,-0.0269,0.00953,0.00529,-0.0002,0.8482,0.8424 0.000,0.0000,0.00950,0.00523,0.0000,0.8458,0.8458 0.250,0.0269,0.00953,0.00528,0.0002,0.8424,0.8481 0.500,0.0533,0.00953,0.00532,0.0004,0.8381,0.8509 0.750,0.0806,0.00949,0.00528,0.0005,0.8347,0.8541 1.000,0.1078,0.00942,0.00518,0.0006,0.8317,0.8575 1.250,0.1326,0.00933,0.00513,0.0012,0.8261,0.8602 1.500,0.1608,0.00915,0.00497,0.0013,0.8198,0.8622 1.750,0.1890,0.00902,0.00485,0.0014,0.8143,0.8645 2.000,0.2148,0.00887,0.00473,0.0019,0.8068,0.8673 2.250,0.2421,0.00871,0.00457,0.0021,0.8006,0.8703 2.500,0.2664,0.00857,0.00448,0.0029,0.7922,0.8734 2.750,0.2928,0.00838,0.00433,0.0034,0.7826,0.8753 3.000,0.3197,0.00822,0.00421,0.0037,0.7726,0.8774 3.250,0.3432,0.00801,0.00401,0.0049,0.7486,0.8798 3.500,0.3658,0.00790,0.00386,0.0062,0.7123,0.8826 3.750,0.3852,0.00797,0.00374,0.0081,0.6568,0.8856 4.000,0.3978,0.00834,0.00375,0.0112,0.5696,0.8884 4.250,0.4056,0.00898,0.00393,0.0151,0.4579,0.8914 4.500,0.4102,0.00985,0.00423,0.0192,0.3233,0.8949 4.750,0.4170,0.01070,0.00455,0.0227,0.2023,0.8986 5.000,0.4262,0.01150,0.00487,0.0258,0.1006,0.9017 5.250,0.4378,0.01229,0.00534,0.0286,0.0365,0.9046 5.500,0.4554,0.01275,0.00582,0.0304,0.0288,0.9073 5.750,0.4731,0.01317,0.00631,0.0322,0.0256,0.9101 6.000,0.4916,0.01348,0.00664,0.0338,0.0223,0.9131 6.250,0.5043,0.01417,0.00738,0.0364,0.0199,0.9161 6.500,0.5173,0.01507,0.00840,0.0389,0.0188,0.9190 6.750,0.5363,0.01553,0.00893,0.0403,0.0183,0.9219 7.000,0.5547,0.01609,0.00956,0.0419,0.0170,0.9253 7.250,0.5744,0.01706,0.01061,0.0431,0.0171,0.9280 7.500,0.5993,0.01809,0.01174,0.0433,0.0163,0.9302 7.750,0.6277,0.01951,0.01329,0.0428,0.0162,0.9320 8.000,0.6574,0.02159,0.01560,0.0423,0.0158,0.9339 8.250,0.6752,0.02153,0.01554,0.0434,0.0142,0.9379 8.500,0.6988,0.02309,0.01727,0.0436,0.0140,0.9408 8.750,0.7217,0.02629,0.02087,0.0443,0.0145,0.9434