Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-pfcm-il-500000 Airfoil,pfcm-il Reynolds number,500000 Ncrit,0 Mach,0 Max Cl/Cd,78.7423 Max Cl/Cd alpha,3 Url,http://airfoiltools.com/polar/csv?polar=xf-pfcm-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -11.500,-0.4537,0.11976,0.11758,-0.0086,1.0000,0.0127 -11.250,-0.4569,0.11497,0.11280,-0.0096,1.0000,0.0130 -11.000,-0.4555,0.11138,0.10921,-0.0101,1.0000,0.0133 -10.750,-0.4536,0.10784,0.10568,-0.0108,1.0000,0.0136 -9.750,-0.5782,0.10190,0.09968,-0.0055,1.0000,0.0129 -9.500,-0.5797,0.09704,0.09483,-0.0078,1.0000,0.0131 -9.250,-0.5786,0.09287,0.09068,-0.0098,1.0000,0.0133 -5.750,-0.4669,0.01503,0.01123,-0.0363,0.9962,0.0226 -5.500,-0.4376,0.01288,0.00895,-0.0383,0.9940,0.0246 -5.000,-0.4114,0.01906,0.01376,-0.0350,0.9955,0.0187 -4.750,-0.3774,0.01709,0.01148,-0.0363,0.9934,0.0194 -4.500,-0.3434,0.01556,0.00969,-0.0376,0.9908,0.0211 -4.250,-0.3102,0.01342,0.00736,-0.0388,0.9887,0.0218 -4.000,-0.2755,0.01211,0.00597,-0.0405,0.9869,0.0227 -3.750,-0.2414,0.01133,0.00513,-0.0420,0.9839,0.0244 -3.500,-0.2067,0.01058,0.00433,-0.0436,0.9808,0.0256 -3.250,-0.1712,0.00994,0.00361,-0.0454,0.9779,0.0273 -3.000,-0.1374,0.00948,0.00309,-0.0467,0.9737,0.0308 -2.750,-0.1052,0.00888,0.00246,-0.0477,0.9682,0.0474 -2.500,-0.0760,0.00769,0.00206,-0.0488,0.9624,0.2533 -2.250,-0.0508,0.00648,0.00189,-0.0490,0.9548,0.5506 -2.000,-0.0245,0.00619,0.00188,-0.0486,0.9466,0.6406 -1.750,0.0018,0.00605,0.00184,-0.0480,0.9387,0.6900 -1.500,0.0276,0.00598,0.00179,-0.0474,0.9288,0.7162 -1.250,0.0528,0.00589,0.00178,-0.0466,0.9195,0.7533 -1.000,0.0770,0.00578,0.00177,-0.0454,0.9106,0.7946 -0.750,0.1022,0.00568,0.00172,-0.0446,0.9002,0.8181 -0.500,0.1278,0.00559,0.00167,-0.0439,0.8900,0.8396 -0.250,0.1529,0.00551,0.00163,-0.0431,0.8803,0.8617 0.000,0.1773,0.00543,0.00161,-0.0421,0.8702,0.8901 0.250,0.2025,0.00535,0.00160,-0.0411,0.8591,0.9288 0.500,0.2374,0.00532,0.00157,-0.0425,0.8492,0.9692 0.750,0.2775,0.00532,0.00154,-0.0453,0.8396,0.9993 1.000,0.3046,0.00537,0.00153,-0.0452,0.8281,1.0000 1.250,0.3315,0.00541,0.00154,-0.0451,0.8149,1.0000 1.500,0.3582,0.00547,0.00154,-0.0448,0.7987,1.0000 1.750,0.3848,0.00553,0.00155,-0.0445,0.7782,1.0000 2.000,0.4103,0.00565,0.00153,-0.0438,0.7464,1.0000 2.250,0.4360,0.00580,0.00156,-0.0433,0.7081,1.0000 2.500,0.4620,0.00598,0.00161,-0.0429,0.6700,1.0000 2.750,0.4878,0.00622,0.00169,-0.0424,0.6235,1.0000 3.000,0.5134,0.00652,0.00180,-0.0420,0.5699,1.0000 3.250,0.5374,0.00705,0.00199,-0.0415,0.4763,1.0000 3.500,0.5560,0.00860,0.00250,-0.0406,0.2380,1.0000 3.750,0.5760,0.01009,0.00315,-0.0399,0.0570,1.0000 4.000,0.6012,0.01072,0.00370,-0.0395,0.0344,1.0000 4.250,0.6261,0.01137,0.00438,-0.0390,0.0289,1.0000 4.500,0.6506,0.01208,0.00520,-0.0384,0.0272,1.0000 4.750,0.6756,0.01265,0.00584,-0.0380,0.0259,1.0000 5.000,0.7001,0.01335,0.00661,-0.0374,0.0243,1.0000 5.250,0.7247,0.01400,0.00731,-0.0369,0.0222,1.0000 5.500,0.7485,0.01487,0.00823,-0.0362,0.0209,1.0000 5.750,0.7719,0.01593,0.00939,-0.0354,0.0197,1.0000 6.000,0.7915,0.01952,0.01318,-0.0340,0.0175,1.0000 6.250,0.8176,0.01958,0.01334,-0.0337,0.0166,1.0000 6.500,0.8421,0.02105,0.01500,-0.0329,0.0157,1.0000 6.750,0.8654,0.02319,0.01741,-0.0319,0.0149,1.0000 7.000,0.8866,0.02616,0.02074,-0.0305,0.0144,1.0000 7.250,0.9081,0.02759,0.02237,-0.0297,0.0131,1.0000 7.500,0.9298,0.02800,0.02279,-0.0295,0.0119,1.0000 7.750,0.9457,0.03111,0.02627,-0.0279,0.0116,1.0000