Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-kenmar-il-500000 Airfoil,kenmar-il Reynolds number,500000 Ncrit,9 Mach,0 Max Cl/Cd,28.2636 Max Cl/Cd alpha,1.75 Url,http://airfoiltools.com/polar/csv?polar=xf-kenmar-il-500000 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -10.750,0.4521,0.10671,0.10089,-0.1598,0.4559,0.0570 -10.500,0.4631,0.10483,0.09904,-0.1606,0.4556,0.0576 -10.250,0.2449,0.06254,0.05657,-0.1840,0.4572,0.0554 -10.000,0.2663,0.06201,0.05611,-0.1827,0.4568,0.0550 -9.750,0.1944,0.05093,0.04484,-0.1901,0.4570,0.0537 -9.500,0.1436,0.04462,0.03829,-0.1928,0.4569,0.0530 -9.250,0.1199,0.04120,0.03471,-0.1931,0.4567,0.0528 -9.000,0.1093,0.03896,0.03234,-0.1925,0.4565,0.0528 -8.750,0.1049,0.03728,0.03056,-0.1915,0.4563,0.0530 -8.500,0.1019,0.03591,0.02909,-0.1900,0.4561,0.0531 -8.250,0.0972,0.03493,0.02803,-0.1877,0.4559,0.0532 -8.000,0.0934,0.03410,0.02712,-0.1850,0.4557,0.0532 -7.750,0.0989,0.03321,0.02614,-0.1836,0.4554,0.0533 -7.500,0.1086,0.03242,0.02527,-0.1825,0.4551,0.0534 -7.250,0.1214,0.03173,0.02450,-0.1817,0.4548,0.0536 -7.000,0.1364,0.03109,0.02380,-0.1809,0.4545,0.0537 -6.750,0.1528,0.03055,0.02319,-0.1802,0.4542,0.0539 -6.500,0.1704,0.03008,0.02267,-0.1794,0.4539,0.0540 -6.250,0.1887,0.02969,0.02222,-0.1786,0.4535,0.0543 -6.000,0.2077,0.02934,0.02183,-0.1777,0.4532,0.0545 -5.750,0.2272,0.02905,0.02150,-0.1769,0.4528,0.0547 -5.500,0.2476,0.02876,0.02118,-0.1761,0.4523,0.0549 -5.250,0.2688,0.02850,0.02088,-0.1754,0.4517,0.0551 -5.000,0.2906,0.02830,0.02064,-0.1748,0.4511,0.0553 -4.750,0.3115,0.02809,0.02041,-0.1740,0.4507,0.0555 -4.500,0.3292,0.02774,0.02009,-0.1723,0.4503,0.0559 -4.250,0.3481,0.02753,0.01993,-0.1709,0.4499,0.0563 -4.000,0.3688,0.02740,0.01984,-0.1700,0.4495,0.0567 -3.750,0.3913,0.02728,0.01974,-0.1695,0.4490,0.0573 -3.500,0.4142,0.02719,0.01966,-0.1690,0.4484,0.0579 -3.250,0.4378,0.02713,0.01962,-0.1687,0.4479,0.0586 -3.000,0.4616,0.02708,0.01957,-0.1684,0.4474,0.0593 -2.750,0.4852,0.02708,0.01958,-0.1680,0.4469,0.0599 -2.500,0.5094,0.02711,0.01962,-0.1678,0.4465,0.0604 -2.250,0.5345,0.02717,0.01968,-0.1677,0.4461,0.0611 -2.000,0.5599,0.02723,0.01974,-0.1678,0.4457,0.0617 -1.750,0.5866,0.02717,0.01973,-0.1683,0.4453,0.0626 -1.500,0.6145,0.02727,0.01986,-0.1690,0.4448,0.0636 -1.250,0.6429,0.02746,0.02008,-0.1697,0.4443,0.0648 -1.000,0.6715,0.02773,0.02036,-0.1705,0.4438,0.0661 -0.750,0.6995,0.02815,0.02079,-0.1712,0.4433,0.0675 -0.500,0.7276,0.02881,0.02150,-0.1722,0.4426,0.0693 -0.250,0.7269,0.03131,0.02416,-0.1692,0.4407,0.0705 0.000,0.7545,0.03123,0.02412,-0.1697,0.4403,0.0731 0.250,0.7814,0.03127,0.02421,-0.1702,0.4398,0.0764 0.500,0.8053,0.03155,0.02458,-0.1704,0.4393,0.0813 0.750,0.8289,0.03194,0.02507,-0.1706,0.4387,0.0901 1.000,0.8544,0.03235,0.02573,-0.1717,0.4379,0.1251 1.250,0.8965,0.03279,0.02671,-0.1766,0.4368,0.2526 1.500,0.9306,0.03367,0.02799,-0.1800,0.4357,0.3517 1.750,0.9799,0.03467,0.02964,-0.1864,0.4345,0.5336 2.000,0.9663,0.03663,0.03179,-0.1816,0.4329,0.5594 2.250,0.9386,0.03932,0.03464,-0.1756,0.4310,0.5685 2.500,0.9204,0.04191,0.03735,-0.1717,0.4294,0.5819 2.750,0.9188,0.04380,0.03930,-0.1695,0.4282,0.5953 3.000,0.9341,0.04485,0.04033,-0.1689,0.4276,0.6105 3.250,0.9533,0.04535,0.04084,-0.1678,0.4271,0.6219 3.500,0.9693,0.04631,0.04177,-0.1673,0.4264,0.6315 3.750,0.9827,0.04717,0.04264,-0.1659,0.4258,0.6387 4.000,0.9944,0.04812,0.04360,-0.1643,0.4251,0.6464 4.250,1.0015,0.05003,0.04549,-0.1630,0.4242,0.6538 4.500,0.6582,0.09252,0.08857,-0.1643,0.3925,0.5962 4.750,0.6877,0.09227,0.08831,-0.1637,0.3930,0.6164 5.000,0.6310,0.10214,0.09825,-0.1647,0.3825,0.6100 5.250,0.6523,0.10258,0.09871,-0.1640,0.3821,0.6241 5.500,0.6766,0.10288,0.09896,-0.1637,0.3817,0.6356 5.750,0.6964,0.10320,0.09929,-0.1627,0.3813,0.6444 6.000,0.7184,0.10354,0.09959,-0.1619,0.3810,0.6542 6.250,0.7374,0.10393,0.09998,-0.1608,0.3807,0.6622 6.500,0.7512,0.10441,0.10049,-0.1587,0.3802,0.6700 6.750,0.7063,0.11312,0.10930,-0.1601,0.3693,0.6680