Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-fx66h60-il-500000-n5 Airfoil,fx66h60-il Reynolds number,500000 Ncrit,5 Mach,0 Max Cl/Cd,67.8438 Max Cl/Cd alpha,5.25 Url,http://airfoiltools.com/polar/csv?polar=xf-fx66h60-il-500000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.6103,0.09195,0.08985,0.0275,1.0000,0.0038 -7.750,-0.6108,0.08797,0.08591,0.0240,1.0000,0.0042 -7.500,-0.6140,0.08395,0.08190,0.0214,1.0000,0.0042 -6.250,-0.5236,0.05620,0.05417,0.0105,1.0000,0.0093 -6.000,-0.5144,0.05149,0.04938,0.0094,1.0000,0.0093 -5.750,-0.5037,0.04681,0.04460,0.0087,1.0000,0.0093 -5.500,-0.4911,0.04221,0.03989,0.0083,1.0000,0.0093 -4.500,-0.4549,0.03635,0.03307,0.0096,1.0000,0.0076 -4.250,-0.4341,0.03241,0.02888,0.0107,1.0000,0.0068 -4.000,-0.3905,0.02731,0.02293,0.0079,0.7929,0.0063 -3.750,-0.3694,0.02419,0.01926,0.0100,0.7302,0.0064 -3.500,-0.3461,0.02144,0.01600,0.0118,0.6824,0.0070 -3.250,-0.3216,0.01926,0.01332,0.0132,0.6405,0.0077 -3.000,-0.2956,0.01857,0.01233,0.0140,0.6009,0.0090 -2.500,-0.2443,0.01560,0.00865,0.0157,0.5413,0.0091 -2.250,-0.2184,0.01410,0.00685,0.0165,0.5158,0.0089 -2.000,-0.1925,0.01296,0.00548,0.0173,0.4927,0.0087 -1.750,-0.1670,0.01206,0.00439,0.0180,0.4731,0.0086 -1.500,-0.1417,0.01134,0.00351,0.0187,0.4545,0.0086 -1.250,-0.1164,0.01077,0.00276,0.0194,0.4370,0.0086 -1.000,-0.0907,0.01037,0.00222,0.0200,0.4206,0.0087 -0.750,-0.0644,0.01008,0.00179,0.0205,0.4064,0.0091 -0.500,-0.0379,0.00987,0.00142,0.0209,0.3925,0.0106 -0.250,-0.0112,0.00971,0.00123,0.0213,0.3789,0.0239 0.250,0.0146,0.00678,0.00117,0.0273,0.3599,0.9046 0.500,0.0398,0.00687,0.00126,0.0287,0.3501,0.9520 0.750,0.0811,0.00707,0.00134,0.0263,0.3380,0.9710 1.000,0.1173,0.00717,0.00134,0.0245,0.3268,0.9744 1.250,0.1476,0.00723,0.00132,0.0240,0.3178,0.9760 1.500,0.1771,0.00730,0.00131,0.0236,0.3098,0.9777 1.750,0.2060,0.00737,0.00132,0.0233,0.3017,0.9796 2.000,0.2344,0.00744,0.00134,0.0231,0.2936,0.9817 2.500,0.2962,0.00759,0.00141,0.0217,0.2791,0.9837 3.000,0.3574,0.00776,0.00155,0.0203,0.2666,0.9865 3.250,0.3873,0.00787,0.00164,0.0198,0.2600,0.9881 3.500,0.4169,0.00796,0.00174,0.0193,0.2540,0.9898 3.750,0.4461,0.00807,0.00186,0.0189,0.2484,0.9916 4.000,0.4752,0.00818,0.00203,0.0186,0.2436,0.9935 4.250,0.5053,0.00829,0.00218,0.0180,0.2380,0.9951 4.500,0.5355,0.00844,0.00235,0.0173,0.2325,0.9969 4.750,0.5654,0.00857,0.00249,0.0167,0.2179,0.9986 5.000,0.5943,0.00877,0.00264,0.0163,0.1948,1.0000 5.250,0.6167,0.00909,0.00284,0.0172,0.1584,1.0000 5.500,0.6335,0.01062,0.00377,0.0184,0.0283,1.0000 5.750,0.6553,0.01120,0.00433,0.0194,0.0118,1.0000 6.000,0.6780,0.01167,0.00493,0.0204,0.0085,1.0000 6.250,0.7008,0.01222,0.00560,0.0213,0.0065,1.0000 6.500,0.7227,0.01303,0.00655,0.0222,0.0053,1.0000 6.750,0.7433,0.01416,0.00787,0.0232,0.0043,1.0000 7.000,0.7672,0.01454,0.00830,0.0238,0.0037,1.0000 7.250,0.7891,0.01545,0.00935,0.0245,0.0033,1.0000 7.500,0.8106,0.01645,0.01049,0.0253,0.0030,1.0000 7.750,0.8322,0.01745,0.01169,0.0260,0.0026,1.0000 8.000,0.8533,0.01853,0.01289,0.0266,0.0024,1.0000 8.250,0.8740,0.01966,0.01415,0.0272,0.0021,1.0000 8.500,0.8911,0.02161,0.01630,0.0280,0.0019,1.0000 8.750,0.9041,0.02453,0.01954,0.0292,0.0018,1.0000 9.000,0.9132,0.02829,0.02371,0.0303,0.0017,1.0000 9.500,0.9245,0.03559,0.03171,0.0315,0.0017,1.0000 9.750,0.9231,0.03938,0.03582,0.0315,0.0017,1.0000