Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-naca65210-il-500000 Airfoil,naca65210-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,72.9362 Max Cl/Cd alpha,3.25 Url,http://airfoiltools.com/polar/csv?polar=xf-naca65210-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -10.250,-0.5299,0.09138,0.08908,-0.0312,1.0000,0.0185 -10.000,-0.5324,0.08480,0.08252,-0.0359,1.0000,0.0185 -9.750,-0.5417,0.07705,0.07473,-0.0426,1.0000,0.0185 -6.750,-0.5414,0.02522,0.02030,-0.0449,0.9826,0.0193 -6.500,-0.5129,0.02228,0.01700,-0.0457,0.9772,0.0192 -6.250,-0.4812,0.02139,0.01616,-0.0477,0.9731,0.0212 -6.000,-0.4485,0.01871,0.01313,-0.0489,0.9697,0.0213 -5.750,-0.4204,0.01717,0.01139,-0.0490,0.9621,0.0220 -5.500,-0.3896,0.01583,0.00989,-0.0497,0.9567,0.0228 -5.250,-0.3630,0.01497,0.00892,-0.0494,0.9482,0.0241 -5.000,-0.3355,0.01439,0.00824,-0.0493,0.9410,0.0254 -4.750,-0.3106,0.01390,0.00766,-0.0487,0.9317,0.0260 -4.500,-0.2893,0.01225,0.00591,-0.0475,0.9233,0.0273 -4.250,-0.2666,0.01145,0.00506,-0.0466,0.9148,0.0291 -4.000,-0.2421,0.01103,0.00462,-0.0461,0.9062,0.0316 -3.500,-0.1917,0.01029,0.00373,-0.0451,0.8903,0.0359 -3.250,-0.1669,0.00974,0.00309,-0.0446,0.8834,0.0408 -3.000,-0.1407,0.00946,0.00278,-0.0443,0.8754,0.0476 -2.750,-0.1157,0.00886,0.00239,-0.0440,0.8684,0.1076 -2.500,-0.0987,0.00675,0.00192,-0.0435,0.8600,0.5509 -2.250,-0.0732,0.00652,0.00191,-0.0430,0.8534,0.6358 -2.000,-0.0463,0.00647,0.00189,-0.0427,0.8462,0.6719 -1.750,-0.0199,0.00645,0.00193,-0.0423,0.8400,0.7056 -1.500,0.0063,0.00647,0.00200,-0.0417,0.8326,0.7371 -1.250,0.0333,0.00652,0.00203,-0.0414,0.8268,0.7552 -1.000,0.0604,0.00653,0.00206,-0.0411,0.8196,0.7686 -0.750,0.0878,0.00655,0.00205,-0.0409,0.8137,0.7784 -0.500,0.1158,0.00655,0.00203,-0.0410,0.8068,0.7856 -0.250,0.1436,0.00655,0.00202,-0.0410,0.8007,0.7917 0.000,0.1715,0.00657,0.00202,-0.0410,0.7944,0.7987 0.250,0.1993,0.00657,0.00203,-0.0410,0.7880,0.8051 0.500,0.2271,0.00660,0.00205,-0.0410,0.7822,0.8120 0.750,0.2549,0.00660,0.00208,-0.0411,0.7756,0.8188 1.000,0.2826,0.00664,0.00211,-0.0410,0.7701,0.8257 1.250,0.3103,0.00665,0.00217,-0.0410,0.7632,0.8328 1.500,0.3377,0.00668,0.00221,-0.0409,0.7565,0.8398 1.750,0.3644,0.00666,0.00221,-0.0405,0.7437,0.8472 2.000,0.3904,0.00666,0.00219,-0.0400,0.7276,0.8547 2.250,0.4165,0.00665,0.00221,-0.0395,0.7096,0.8622 2.500,0.4415,0.00668,0.00219,-0.0387,0.6813,0.8701 2.750,0.4666,0.00674,0.00222,-0.0380,0.6549,0.8779 3.000,0.4919,0.00684,0.00228,-0.0374,0.6251,0.8868 3.250,0.5142,0.00705,0.00237,-0.0362,0.5671,0.8949 3.500,0.5272,0.00823,0.00270,-0.0337,0.3637,0.9053 3.750,0.5348,0.01022,0.00347,-0.0309,0.0876,0.9176 4.000,0.5542,0.01084,0.00391,-0.0294,0.0455,0.9294 4.250,0.5746,0.01118,0.00431,-0.0278,0.0381,0.9419 4.500,0.5954,0.01152,0.00471,-0.0264,0.0336,0.9563 4.750,0.6191,0.01233,0.00561,-0.0258,0.0298,0.9720 5.000,0.6527,0.01287,0.00621,-0.0274,0.0282,0.9868 5.250,0.6813,0.01346,0.00683,-0.0280,0.0261,1.0000 5.500,0.7058,0.01405,0.00745,-0.0278,0.0243,1.0000 5.750,0.7289,0.01489,0.00831,-0.0274,0.0231,1.0000 6.000,0.7500,0.01635,0.00980,-0.0265,0.0220,1.0000 6.250,0.7734,0.01856,0.01209,-0.0260,0.0213,1.0000 6.500,0.7993,0.01929,0.01294,-0.0258,0.0208,1.0000 6.750,0.8248,0.02010,0.01386,-0.0255,0.0199,1.0000 7.000,0.8500,0.02139,0.01529,-0.0251,0.0191,1.0000 7.250,0.8744,0.02317,0.01726,-0.0246,0.0186,1.0000 7.500,0.8973,0.02545,0.01980,-0.0238,0.0184,1.0000 7.750,0.9169,0.02886,0.02359,-0.0225,0.0186,1.0000 8.000,0.9327,0.03235,0.02748,-0.0207,0.0188,1.0000 8.250,0.9373,0.03826,0.03385,-0.0182,0.0204,1.0000 11.750,0.6794,0.10742,0.10550,-0.0197,0.0213,1.0000 12.000,0.6678,0.11667,0.11476,-0.0251,0.0213,1.0000