Xfoil polar. Reynolds number fixed. Mach number fixed Polar key,xf-usa31-il-50000-n5 Airfoil,usa31-il Reynolds number,50000 Ncrit,5 Mach,0 Max Cl/Cd,14.0868 Max Cl/Cd alpha,5.75 Url,http://airfoiltools.com/polar/csv?polar=xf-usa31-il-50000-n5 Alpha,Cl,Cd,Cdp,Cm,Top_Xtr,Bot_Xtr -8.000,-0.0368,0.12578,0.11907,-0.0748,0.8820,0.1333 -7.750,-0.0456,0.12589,0.11922,-0.0770,0.8750,0.1358 -7.500,-0.0669,0.12650,0.11991,-0.0751,0.8641,0.1363 -7.250,-0.0454,0.12150,0.11492,-0.0765,0.8603,0.1374 -7.000,-0.0278,0.11748,0.11089,-0.0758,0.8547,0.1394 -6.750,-0.0231,0.11524,0.10866,-0.0748,0.8471,0.1414 -6.500,-0.0108,0.11252,0.10593,-0.0762,0.8428,0.1440 -6.250,-0.0244,0.11181,0.10528,-0.0727,0.8318,0.1457 -6.000,-0.0216,0.10983,0.10331,-0.0737,0.8265,0.1489 -5.750,-0.0413,0.10989,0.10343,-0.0716,0.8145,0.1514 -5.500,-0.0367,0.10815,0.10164,-0.0772,0.8085,0.1529 -5.250,-0.0494,0.10750,0.10103,-0.0760,0.7964,0.1531 -4.750,-0.0282,0.10056,0.09415,-0.0722,0.7851,0.1556 -4.250,-0.0015,0.08918,0.08246,-0.0829,0.7733,0.0961 -4.000,-0.0064,0.08786,0.08115,-0.0801,0.7626,0.0917 -3.750,0.0193,0.08198,0.07505,-0.0875,0.7576,0.0827 -3.500,0.0317,0.07984,0.07286,-0.0873,0.7511,0.0813 -3.250,0.0433,0.07752,0.07049,-0.0878,0.7429,0.0796 -2.750,0.1007,0.06705,0.05945,-0.0991,0.7322,0.0729 -2.500,0.1215,0.06429,0.05651,-0.1006,0.7253,0.0723 -2.250,0.1588,0.05930,0.05105,-0.1055,0.7219,0.0722 -2.000,0.1858,0.05564,0.04681,-0.1081,0.7163,0.0725 -1.750,0.2036,0.05370,0.04441,-0.1080,0.7084,0.0727 -1.500,0.2362,0.05135,0.04153,-0.1093,0.7045,0.0728 -1.250,0.2562,0.05035,0.04016,-0.1085,0.6977,0.0730 -1.000,0.2764,0.04960,0.03905,-0.1077,0.6903,0.0733 -0.750,0.3091,0.04839,0.03761,-0.1082,0.6866,0.0740 -0.500,0.3231,0.04848,0.03756,-0.1066,0.6779,0.0748 -0.250,0.3483,0.04800,0.03691,-0.1062,0.6718,0.0760 0.000,0.3822,0.04714,0.03586,-0.1066,0.6684,0.0789 0.250,0.3933,0.04788,0.03646,-0.1049,0.6584,0.0811 0.500,0.4269,0.04755,0.03593,-0.1057,0.6533,0.0846 0.750,0.4678,0.04685,0.03511,-0.1074,0.6502,0.0888 1.250,0.5130,0.04780,0.03592,-0.1069,0.6348,0.0980 1.500,0.5573,0.04706,0.03524,-0.1091,0.6320,0.1170 2.000,0.5818,0.04909,0.03787,-0.1049,0.6157,0.2357 2.250,0.6054,0.04922,0.03781,-0.1028,0.6127,0.2943 2.750,0.6219,0.05181,0.04024,-0.0978,0.5959,0.3396 3.000,0.6561,0.05126,0.03955,-0.0979,0.5936,0.3687 3.500,0.6833,0.05361,0.04173,-0.0961,0.5767,0.4040 3.750,0.7253,0.05285,0.04075,-0.0978,0.5747,0.4163 4.000,0.7139,0.05622,0.04415,-0.0952,0.5604,0.4189 4.250,0.7513,0.05575,0.04349,-0.0963,0.5577,0.4271 4.750,0.7768,0.05894,0.04661,-0.0952,0.5412,0.4349 5.000,0.8134,0.05840,0.04594,-0.0960,0.5388,0.4412 5.500,0.8315,0.06217,0.04972,-0.0943,0.5222,0.4480 5.750,0.8669,0.06154,0.04902,-0.0948,0.5200,0.4523 6.250,0.8779,0.06595,0.05346,-0.0925,0.5034,0.4578 6.750,0.8883,0.07054,0.05813,-0.0906,0.4872,0.4648 7.000,0.9192,0.07014,0.05771,-0.0905,0.4848,0.4705 7.500,0.9249,0.07531,0.06298,-0.0884,0.4685,0.4757 7.750,0.9563,0.07472,0.06241,-0.0883,0.4663,0.4813 8.000,0.9299,0.08067,0.06846,-0.0867,0.4526,0.4818 8.250,0.9579,0.08046,0.06829,-0.0864,0.4498,0.4895 8.750,0.9598,0.08627,0.07430,-0.0848,0.4337,0.5009 9.000,0.9900,0.08565,0.07385,-0.0845,0.4312,0.5213 9.500,1.0038,0.09175,0.08045,-0.0861,0.4146,1.0000 10.000,1.0025,0.09806,0.08682,-0.0846,0.3984,1.0000 10.250,1.0291,0.09779,0.08652,-0.0839,0.3957,1.0000 10.750,1.0257,0.10447,0.09327,-0.0828,0.3793,1.0000 11.000,1.0534,0.10391,0.09271,-0.0820,0.3770,1.0000 11.250,1.0229,0.11124,0.10014,-0.0821,0.3635,1.0000 11.500,1.0476,0.11104,0.09993,-0.0813,0.3606,1.0000 12.000,1.0416,0.11839,0.10739,-0.0811,0.3448,1.0000 12.250,1.0669,0.11804,0.10705,-0.0802,0.3423,1.0000 12.500,1.0398,0.12525,0.11435,-0.0811,0.3298,1.0000 12.750,1.0597,0.12568,0.11480,-0.0805,0.3266,1.0000