Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-goe445-il-100000-n5 Airfoil,goe445-il Reynolds number,100000 Ncrit,5 Mach,0 Max Cl/Cd,30.7734 Max Cl/Cd alpha,2.5 Url,http://airfoiltools.com/polar/csv?polar=xf-goe445-il-100000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -9.000,-0.5351,0.08875,0.08424,-0.0032,1.0000,0.0514 -8.750,-0.5399,0.08402,0.07955,-0.0052,1.0000,0.0523 -8.250,-0.6446,0.08440,0.07977,-0.0085,1.0000,0.0480 -6.750,-0.6385,0.05445,0.04891,-0.0165,1.0000,0.0240 -6.500,-0.6309,0.05025,0.04452,-0.0158,1.0000,0.0223 -6.250,-0.6207,0.04600,0.03995,-0.0147,1.0000,0.0205 -6.000,-0.6076,0.04143,0.03485,-0.0129,1.0000,0.0181 -5.750,-0.5870,0.03908,0.03189,-0.0108,1.0000,0.0164 -5.500,-0.5727,0.03517,0.02764,-0.0093,1.0000,0.0159 -5.250,-0.5554,0.03195,0.02398,-0.0076,1.0000,0.0157 -5.000,-0.5358,0.02909,0.02067,-0.0058,1.0000,0.0155 -4.750,-0.5144,0.02655,0.01769,-0.0042,1.0000,0.0155 -4.500,-0.4914,0.02428,0.01499,-0.0027,1.0000,0.0158 -4.250,-0.4685,0.02213,0.01256,-0.0013,1.0000,0.0173 -4.000,-0.4468,0.02030,0.01064,-0.0001,1.0000,0.0195 -3.750,-0.4254,0.01879,0.00903,0.0015,1.0000,0.0207 -3.500,-0.4050,0.01753,0.00761,0.0033,1.0000,0.0227 -3.250,-0.3846,0.01647,0.00640,0.0048,1.0000,0.0279 -3.000,-0.3631,0.01557,0.00528,0.0063,1.0000,0.0352 -2.750,-0.3468,0.01359,0.00424,0.0081,1.0000,0.2062 -2.500,-0.3379,0.01099,0.00445,0.0133,1.0000,0.7974 -2.250,-0.2873,0.01109,0.00436,0.0104,1.0000,0.9006 -2.000,-0.2455,0.01110,0.00402,0.0077,1.0000,0.9281 -1.750,-0.2005,0.01113,0.00378,0.0042,1.0000,0.9539 -1.500,-0.1449,0.01116,0.00356,-0.0016,1.0000,0.9787 -1.250,-0.0895,0.01107,0.00323,-0.0077,1.0000,0.9971 -1.000,-0.0662,0.01095,0.00303,-0.0074,1.0000,1.0000 -0.750,-0.0500,0.01086,0.00288,-0.0055,1.0000,1.0000 -0.500,-0.0336,0.01079,0.00277,-0.0037,1.0000,1.0000 -0.250,-0.0168,0.01076,0.00271,-0.0018,1.0000,1.0000 0.000,0.0000,0.01074,0.00269,0.0000,1.0000,1.0000 0.250,0.0168,0.01076,0.00271,0.0018,1.0000,1.0000 0.500,0.0336,0.01079,0.00277,0.0037,1.0000,1.0000 0.750,0.0500,0.01086,0.00288,0.0055,1.0000,1.0000 1.000,0.0662,0.01096,0.00303,0.0074,1.0000,1.0000 1.250,0.0894,0.01107,0.00323,0.0077,0.9971,1.0000 1.500,0.1450,0.01116,0.00356,0.0016,0.9787,1.0000 1.750,0.2003,0.01113,0.00378,-0.0042,0.9539,1.0000 2.000,0.2453,0.01110,0.00402,-0.0077,0.9282,1.0000 2.250,0.2872,0.01109,0.00436,-0.0104,0.9008,1.0000 2.500,0.3382,0.01099,0.00445,-0.0134,0.7974,1.0000 2.750,0.3472,0.01359,0.00425,-0.0082,0.2057,1.0000 3.000,0.3634,0.01559,0.00529,-0.0064,0.0350,1.0000 3.250,0.3850,0.01648,0.00641,-0.0049,0.0278,1.0000 3.500,0.4054,0.01756,0.00764,-0.0033,0.0225,1.0000 3.750,0.4258,0.01880,0.00904,-0.0016,0.0207,1.0000 4.000,0.4471,0.02030,0.01064,0.0000,0.0195,1.0000 4.250,0.4690,0.02209,0.01253,0.0013,0.0174,1.0000 4.500,0.4917,0.02429,0.01500,0.0026,0.0158,1.0000 4.750,0.5147,0.02653,0.01767,0.0041,0.0156,1.0000 5.000,0.5361,0.02907,0.02065,0.0058,0.0155,1.0000 5.250,0.5556,0.03194,0.02397,0.0075,0.0157,1.0000 5.500,0.5729,0.03517,0.02763,0.0092,0.0159,1.0000 5.750,0.5873,0.03897,0.03177,0.0107,0.0164,1.0000 6.000,0.6077,0.04130,0.03470,0.0128,0.0180,1.0000 6.250,0.6208,0.04596,0.03992,0.0147,0.0205,1.0000 6.500,0.6309,0.05023,0.04450,0.0158,0.0224,1.0000 6.750,0.6386,0.05435,0.04879,0.0165,0.0241,1.0000 9.250,0.6415,0.10235,0.09753,0.0024,0.0437,1.0000 9.500,0.6373,0.10687,0.10199,-0.0027,0.0431,1.0000 9.750,0.6333,0.11113,0.10617,-0.0075,0.0405,1.0000