Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca65209-il-500000 Airfoil,naca65209-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,71.3154 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-naca65209-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -7.750,-0.5860,0.05117,0.04835,-0.0420,1.0000,0.0168 -7.500,-0.5937,0.04627,0.04330,-0.0404,1.0000,0.0173 -7.250,-0.5904,0.04421,0.04121,-0.0385,1.0000,0.0178 -7.000,-0.5908,0.04230,0.03922,-0.0354,1.0000,0.0181 -6.750,-0.5696,0.03963,0.03640,-0.0369,0.9973,0.0192 -6.500,-0.5397,0.03653,0.03304,-0.0394,0.9938,0.0215 -6.250,-0.5018,0.03665,0.03277,-0.0402,0.9898,0.0243 -5.500,-0.4199,0.01976,0.01447,-0.0446,0.9776,0.0200 -5.250,-0.3869,0.01737,0.01177,-0.0457,0.9740,0.0202 -5.000,-0.3525,0.01616,0.01037,-0.0471,0.9707,0.0219 -4.750,-0.3214,0.01467,0.00871,-0.0477,0.9653,0.0226 -4.500,-0.2907,0.01369,0.00762,-0.0483,0.9592,0.0235 -4.250,-0.2601,0.01317,0.00701,-0.0488,0.9532,0.0243 -4.000,-0.2369,0.01141,0.00519,-0.0481,0.9445,0.0268 -3.750,-0.2117,0.01077,0.00449,-0.0477,0.9359,0.0287 -3.500,-0.1861,0.01029,0.00395,-0.0472,0.9281,0.0309 -3.250,-0.1610,0.00989,0.00349,-0.0467,0.9191,0.0335 -3.000,-0.1355,0.00949,0.00300,-0.0462,0.9114,0.0373 -2.750,-0.1100,0.00910,0.00257,-0.0458,0.9027,0.0449 -2.500,-0.0843,0.00866,0.00221,-0.0454,0.8947,0.0778 -2.250,-0.0669,0.00645,0.00178,-0.0449,0.8865,0.5712 -2.000,-0.0418,0.00621,0.00179,-0.0443,0.8783,0.6605 -1.500,0.0099,0.00611,0.00184,-0.0431,0.8631,0.7437 -1.250,0.0359,0.00613,0.00187,-0.0424,0.8565,0.7687 -1.000,0.0624,0.00615,0.00191,-0.0420,0.8484,0.7880 -0.750,0.0890,0.00618,0.00192,-0.0416,0.8417,0.8024 -0.500,0.1161,0.00617,0.00191,-0.0414,0.8340,0.8102 -0.250,0.1438,0.00619,0.00188,-0.0413,0.8274,0.8184 0.000,0.1710,0.00618,0.00189,-0.0411,0.8197,0.8257 0.250,0.1985,0.00620,0.00189,-0.0410,0.8131,0.8336 0.500,0.2257,0.00621,0.00192,-0.0409,0.8055,0.8414 0.750,0.2529,0.00623,0.00194,-0.0407,0.7989,0.8491 1.000,0.2801,0.00624,0.00198,-0.0406,0.7913,0.8574 1.250,0.3069,0.00627,0.00203,-0.0403,0.7840,0.8651 1.750,0.3588,0.00628,0.00204,-0.0392,0.7574,0.8818 2.000,0.3840,0.00627,0.00204,-0.0384,0.7374,0.8907 2.250,0.4081,0.00630,0.00200,-0.0374,0.7067,0.9001 2.500,0.4317,0.00637,0.00203,-0.0363,0.6756,0.9090 2.750,0.4554,0.00646,0.00207,-0.0353,0.6401,0.9190 3.000,0.4771,0.00669,0.00212,-0.0339,0.5797,0.9302 3.250,0.4871,0.00797,0.00242,-0.0307,0.3425,0.9444 3.500,0.4967,0.00986,0.00311,-0.0282,0.0604,0.9613 3.750,0.5256,0.01041,0.00360,-0.0286,0.0388,0.9749 4.000,0.5599,0.01087,0.00411,-0.0303,0.0328,0.9876 4.250,0.5877,0.01176,0.00506,-0.0308,0.0282,1.0000 4.500,0.6131,0.01221,0.00554,-0.0306,0.0266,1.0000 4.750,0.6376,0.01285,0.00624,-0.0302,0.0251,1.0000 5.000,0.6617,0.01357,0.00701,-0.0298,0.0237,1.0000 5.250,0.6856,0.01442,0.00790,-0.0292,0.0226,1.0000 5.500,0.7096,0.01532,0.00881,-0.0288,0.0213,1.0000 5.750,0.7321,0.01730,0.01084,-0.0281,0.0198,1.0000 6.000,0.7570,0.01971,0.01343,-0.0276,0.0192,1.0000 6.250,0.7826,0.02074,0.01461,-0.0272,0.0188,1.0000 6.500,0.8073,0.02255,0.01664,-0.0266,0.0184,1.0000 6.750,0.8312,0.02433,0.01866,-0.0259,0.0178,1.0000 7.000,0.8539,0.02631,0.02090,-0.0250,0.0170,1.0000 7.250,0.8708,0.03037,0.02540,-0.0232,0.0177,1.0000 11.000,0.6775,0.10293,0.10101,-0.0217,0.0193,1.0000 11.250,0.6695,0.11103,0.10912,-0.0262,0.0193,1.0000