XFOIL Version 6.96 Calculated polar for: EPPLER 339 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.2836 0.09592 0.09149 -0.0373 1.0000 0.0470 -8.500 -0.2968 0.09252 0.08821 -0.0407 1.0000 0.0475 -8.250 -0.3149 0.08934 0.08515 -0.0432 1.0000 0.0476 -8.000 -0.2946 0.08644 0.08233 -0.0392 0.9993 0.0491 -7.750 -0.2798 0.08187 0.07777 -0.0444 0.9612 0.0504 -7.500 -0.2646 0.07650 0.07230 -0.0528 0.9103 0.0532 -7.250 -0.2642 0.07126 0.06655 -0.0626 0.8693 0.0552 -7.000 -0.2377 0.06624 0.06153 -0.0648 0.8416 0.0561 -6.750 -0.2219 0.06279 0.05792 -0.0657 0.8137 0.0573 -6.500 -0.2122 0.05992 0.05485 -0.0658 0.7891 0.0585 -6.250 -0.2039 0.05711 0.05182 -0.0653 0.7684 0.0599 -5.750 -0.1863 0.04797 0.04190 -0.0626 0.7376 0.0330 -5.250 -0.1617 0.04068 0.03372 -0.0585 0.7100 0.0259 -5.000 -0.1456 0.03839 0.03115 -0.0571 0.6967 0.0253 -4.750 -0.1286 0.03596 0.02836 -0.0554 0.6848 0.0247 -4.500 -0.1104 0.03360 0.02559 -0.0536 0.6726 0.0240 -4.250 -0.0906 0.03118 0.02269 -0.0517 0.6615 0.0234 -4.000 -0.0687 0.02906 0.02008 -0.0501 0.6512 0.0231 -3.750 -0.0453 0.02730 0.01792 -0.0488 0.6401 0.0230 -3.500 -0.0203 0.02579 0.01604 -0.0478 0.6306 0.0232 -3.250 0.0053 0.02448 0.01446 -0.0470 0.6200 0.0236 -3.000 0.0317 0.02341 0.01312 -0.0463 0.6106 0.0252 -2.750 0.0581 0.02246 0.01197 -0.0457 0.6010 0.0271 -2.500 0.0842 0.02169 0.01107 -0.0452 0.5923 0.0293 -2.250 0.1100 0.02080 0.01005 -0.0444 0.5837 0.0310 -2.000 0.1340 0.02013 0.00932 -0.0434 0.5760 0.0334 -1.750 0.1572 0.01962 0.00876 -0.0424 0.5675 0.0379 -1.500 0.1806 0.01916 0.00819 -0.0413 0.5608 0.0443 -1.250 0.2041 0.01876 0.00775 -0.0403 0.5527 0.0555 -1.000 0.2646 0.01620 0.00816 -0.0448 0.5452 0.8201 -0.750 0.4385 0.01712 0.00825 -0.0702 0.5304 0.9934 -0.500 0.4747 0.01699 0.00787 -0.0722 0.5237 0.9984 -0.250 0.5012 0.01700 0.00774 -0.0723 0.5171 1.0000 0.000 0.5234 0.01708 0.00764 -0.0714 0.5117 1.0000 0.250 0.5456 0.01718 0.00760 -0.0706 0.5062 1.0000 0.500 0.5677 0.01728 0.00761 -0.0697 0.5001 1.0000 0.750 0.5899 0.01739 0.00759 -0.0688 0.4950 1.0000 1.000 0.6123 0.01753 0.00760 -0.0679 0.4903 1.0000 1.250 0.6343 0.01768 0.00771 -0.0671 0.4849 1.0000 1.500 0.6565 0.01782 0.00777 -0.0662 0.4800 1.0000 1.750 0.6790 0.01797 0.00780 -0.0653 0.4758 1.0000 2.000 0.7007 0.01815 0.00796 -0.0644 0.4708 1.0000 2.250 0.7225 0.01834 0.00812 -0.0635 0.4660 1.0000 2.500 0.7446 0.01852 0.00824 -0.0626 0.4618 1.0000 2.750 0.7671 0.01871 0.00833 -0.0617 0.4582 1.0000 3.000 0.7880 0.01895 0.00862 -0.0607 0.4534 1.0000 3.250 0.8092 0.01918 0.00886 -0.0596 0.4487 1.0000 3.500 0.8308 0.01940 0.00904 -0.0587 0.4449 1.0000 3.750 0.8530 0.01963 0.00920 -0.0578 0.4415 1.0000 4.000 0.8728 0.01994 0.00959 -0.0566 0.4371 1.0000 4.250 0.8928 0.02023 0.00993 -0.0554 0.4327 1.0000 4.500 0.9136 0.02049 0.01019 -0.0543 0.4288 1.0000 4.750 0.9353 0.02074 0.01039 -0.0533 0.4255 1.0000 5.000 0.9544 0.02109 0.01083 -0.0520 0.4215 1.0000 5.250 0.9727 0.02146 0.01129 -0.0505 0.4171 1.0000 5.500 0.9921 0.02177 0.01163 -0.0492 0.4132 1.0000 5.750 1.0127 0.02204 0.01189 -0.0480 0.4098 1.0000 6.000 1.0321 0.02239 0.01229 -0.0467 0.4063 1.0000 6.250 1.0474 0.02284 0.01289 -0.0448 0.4017 1.0000 6.500 1.0647 0.02320 0.01332 -0.0432 0.3975 1.0000 6.750 1.0840 0.02350 0.01364 -0.0419 0.3940 1.0000 7.000 1.1041 0.02380 0.01395 -0.0406 0.3907 1.0000 7.250 1.1151 0.02435 0.01470 -0.0381 0.3859 1.0000 7.500 1.1297 0.02476 0.01522 -0.0360 0.3816 1.0000 7.750 1.1475 0.02505 0.01555 -0.0344 0.3778 1.0000 8.000 1.1665 0.02534 0.01585 -0.0330 0.3744 1.0000 8.250 1.1727 0.02596 0.01669 -0.0297 0.3694 1.0000 8.500 1.1846 0.02639 0.01722 -0.0273 0.3649 1.0000 8.750 1.2020 0.02663 0.01750 -0.0256 0.3610 1.0000 9.000 1.2140 0.02705 0.01801 -0.0232 0.3568 1.0000 9.250 1.2180 0.02767 0.01881 -0.0196 0.3517 1.0000 9.500 1.2309 0.02799 0.01921 -0.0174 0.3470 1.0000 9.750 1.2522 0.02811 0.01932 -0.0164 0.3430 1.0000 10.000 1.2496 0.02898 0.02044 -0.0122 0.3372 1.0000 10.250 1.2604 0.02940 0.02096 -0.0099 0.3319 1.0000 10.500 1.2816 0.02950 0.02106 -0.0089 0.3274 1.0000 10.750 1.2748 0.03055 0.02235 -0.0045 0.3214 1.0000 11.000 1.2822 0.03104 0.02293 -0.0019 0.3160 1.0000 11.250 1.2946 0.03143 0.02338 0.0000 0.3110 1.0000 11.500 1.2859 0.03279 0.02494 0.0037 0.3049 1.0000 11.750 1.2962 0.03333 0.02555 0.0054 0.2992 1.0000 12.000 1.2923 0.03478 0.02715 0.0079 0.2933 1.0000 12.250 1.2884 0.03637 0.02888 0.0099 0.2869 1.0000 12.500 1.2946 0.03742 0.02999 0.0111 0.2810 1.0000 12.750 1.2765 0.04054 0.03330 0.0126 0.2741 1.0000 13.000 1.2871 0.04140 0.03419 0.0134 0.2676 1.0000 13.250 1.2576 0.04627 0.03926 0.0138 0.2602 1.0000 13.500 1.2682 0.04725 0.04026 0.0143 0.2534 1.0000 13.750 1.2326 0.05357 0.04675 0.0136 0.2454 1.0000 14.000 1.2400 0.05504 0.04824 0.0138 0.2384 1.0000 14.250 1.2099 0.06131 0.05464 0.0125 0.2300 1.0000 14.500 1.2054 0.06447 0.05785 0.0120 0.2224 1.0000 14.750 1.1974 0.06822 0.06166 0.0112 0.2145 1.0000 15.000 1.1825 0.07310 0.06662 0.0100 0.2066 1.0000 15.250 1.1941 0.07420 0.06774 0.0100 0.1993 1.0000 15.500 1.1704 0.08068 0.07433 0.0080 0.1912 1.0000 15.750 1.1861 0.08119 0.07483 0.0082 0.1840 1.0000 16.000 1.1649 0.08758 0.08136 0.0060 0.1761 1.0000 16.250 1.1714 0.08960 0.08339 0.0055 0.1692 1.0000 16.500 1.1618 0.09433 0.08821 0.0039 0.1617 1.0000 16.750 1.1614 0.09758 0.09149 0.0028 0.1550 1.0000