XFOIL Version 6.96 Calculated polar for: EPPLER 344 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.2582 0.09432 0.09129 -0.0371 1.0000 0.0376 -8.750 -0.2603 0.09122 0.08828 -0.0380 1.0000 0.0380 -8.500 -0.2609 0.08660 0.08374 -0.0436 0.9903 0.0398 -8.250 -0.2527 0.07776 0.07474 -0.0625 0.9241 0.0405 -8.000 -0.2141 0.07038 0.06722 -0.0721 0.8855 0.0418 -7.750 -0.1844 0.06633 0.06292 -0.0771 0.8356 0.0430 -7.500 -0.1838 0.06368 0.06002 -0.0769 0.7984 0.0440 -7.250 -0.1853 0.06104 0.05716 -0.0760 0.7721 0.0450 -7.000 -0.1861 0.05846 0.05436 -0.0749 0.7516 0.0464 -6.750 -0.2007 0.05755 0.05276 -0.0714 0.7359 0.0488 -6.500 -0.1932 0.05276 0.04793 -0.0707 0.7206 0.0496 -6.250 -0.1807 0.04998 0.04513 -0.0698 0.7052 0.0504 -6.000 -0.1690 0.04788 0.04293 -0.0685 0.6915 0.0517 -5.750 -0.1576 0.04588 0.04072 -0.0669 0.6795 0.0537 -5.250 -0.1379 0.04141 0.03556 -0.0624 0.6570 0.0602 -5.000 -0.1217 0.03927 0.03334 -0.0613 0.6463 0.0619 -4.750 -0.1051 0.03760 0.03154 -0.0599 0.6350 0.0651 -4.500 -0.0915 0.03609 0.02950 -0.0572 0.6263 0.0719 -4.250 -0.0727 0.03390 0.02731 -0.0564 0.6161 0.0743 -4.000 -0.0503 0.03622 0.02904 -0.0537 0.6069 0.0837 -3.750 -0.0355 0.03087 0.02379 -0.0533 0.5989 0.0875 -3.500 -0.0139 0.02958 0.02236 -0.0523 0.5908 0.0935 -3.250 0.0182 0.02435 0.01606 -0.0484 0.5842 0.0434 -3.000 0.0479 0.02209 0.01304 -0.0465 0.5776 0.0339 -2.750 0.0752 0.02060 0.01145 -0.0460 0.5689 0.0334 -2.500 0.1033 0.01952 0.01017 -0.0456 0.5620 0.0332 -2.250 0.1307 0.01864 0.00916 -0.0450 0.5548 0.0343 -2.000 0.1563 0.01797 0.00853 -0.0446 0.5480 0.0376 -1.750 0.1823 0.01752 0.00795 -0.0439 0.5423 0.0410 -1.500 0.2046 0.01679 0.00732 -0.0427 0.5355 0.0447 -1.250 0.2267 0.01626 0.00677 -0.0414 0.5299 0.0525 -1.000 0.2481 0.01580 0.00633 -0.0400 0.5245 0.0737 -0.750 0.4410 0.01592 0.00883 -0.0658 0.5122 0.9724 -0.500 0.5460 0.01494 0.00756 -0.0815 0.5036 1.0000 -0.250 0.5681 0.01496 0.00748 -0.0807 0.4986 1.0000 0.000 0.5907 0.01505 0.00741 -0.0800 0.4946 1.0000 0.250 0.6128 0.01514 0.00744 -0.0793 0.4902 1.0000 0.500 0.6350 0.01521 0.00747 -0.0785 0.4858 1.0000 0.750 0.6577 0.01530 0.00748 -0.0778 0.4818 1.0000 1.000 0.6807 0.01543 0.00748 -0.0771 0.4783 1.0000 1.250 0.7031 0.01557 0.00760 -0.0764 0.4744 1.0000 1.500 0.7252 0.01568 0.00771 -0.0756 0.4701 1.0000 1.750 0.7479 0.01581 0.00779 -0.0748 0.4665 1.0000 2.000 0.7711 0.01596 0.00786 -0.0742 0.4633 1.0000 2.250 0.7947 0.01620 0.00800 -0.0736 0.4602 1.0000 2.500 0.8160 0.01634 0.00821 -0.0726 0.4564 1.0000 2.750 0.8380 0.01650 0.00839 -0.0718 0.4525 1.0000 3.000 0.8608 0.01667 0.00853 -0.0711 0.4494 1.0000 3.250 0.8842 0.01687 0.00866 -0.0705 0.4465 1.0000 3.500 0.9077 0.01715 0.00888 -0.0699 0.4436 1.0000 3.750 0.9281 0.01736 0.00920 -0.0688 0.4400 1.0000 4.000 0.9495 0.01757 0.00946 -0.0678 0.4365 1.0000 4.250 0.9718 0.01778 0.00967 -0.0670 0.4335 1.0000 4.500 0.9951 0.01798 0.00982 -0.0664 0.4305 1.0000 4.750 1.0191 0.01830 0.01008 -0.0660 0.4278 1.0000 5.000 1.0378 0.01858 0.01050 -0.0646 0.4244 1.0000 5.250 1.0578 0.01886 0.01086 -0.0634 0.4210 1.0000 5.500 1.0790 0.01909 0.01112 -0.0624 0.4178 1.0000 5.750 1.1017 0.01930 0.01132 -0.0617 0.4148 1.0000 6.000 1.1259 0.01963 0.01158 -0.0613 0.4122 1.0000 6.250 1.1428 0.02001 0.01211 -0.0596 0.4088 1.0000 6.500 1.1605 0.02034 0.01257 -0.0581 0.4051 1.0000 6.750 1.1802 0.02061 0.01289 -0.0569 0.4018 1.0000 7.000 1.2023 0.02083 0.01309 -0.0561 0.3988 1.0000 7.250 1.2270 0.02117 0.01337 -0.0558 0.3960 1.0000 7.500 1.2397 0.02161 0.01402 -0.0534 0.3924 1.0000 7.750 1.2552 0.02197 0.01450 -0.0515 0.3885 1.0000 8.000 1.2740 0.02221 0.01479 -0.0501 0.3851 1.0000 8.250 1.2971 0.02239 0.01494 -0.0495 0.3820 1.0000 8.500 1.3154 0.02280 0.01539 -0.0481 0.3786 1.0000 8.750 1.3248 0.02325 0.01604 -0.0452 0.3744 1.0000 9.000 1.3399 0.02351 0.01639 -0.0432 0.3705 1.0000 9.250 1.3610 0.02363 0.01650 -0.0422 0.3671 1.0000 9.500 1.3828 0.02391 0.01676 -0.0414 0.3636 1.0000 9.750 1.3850 0.02440 0.01749 -0.0373 0.3592 1.0000 10.000 1.3960 0.02465 0.01784 -0.0346 0.3550 1.0000 10.250 1.4166 0.02466 0.01783 -0.0335 0.3513 1.0000 10.500 1.4325 0.02495 0.01814 -0.0317 0.3475 1.0000 10.750 1.4283 0.02537 0.01877 -0.0265 0.3429 1.0000 11.000 1.4363 0.02549 0.01896 -0.0232 0.3386 1.0000 11.250 1.4602 0.02537 0.01877 -0.0226 0.3345 1.0000 11.500 1.4531 0.02579 0.01936 -0.0170 0.3303 1.0000 11.750 1.4507 0.02607 0.01976 -0.0122 0.3255 1.0000 12.000 1.4688 0.02600 0.01970 -0.0108 0.3209 1.0000 12.250 1.4767 0.02634 0.02011 -0.0081 0.3163 1.0000 12.500 1.4718 0.02683 0.02076 -0.0035 0.3111 1.0000 12.750 1.4874 0.02686 0.02078 -0.0020 0.3059 1.0000 13.000 1.4892 0.02748 0.02151 0.0011 0.3007 1.0000 13.250 1.4884 0.02819 0.02235 0.0041 0.2948 1.0000 13.500 1.5050 0.02835 0.02248 0.0051 0.2890 1.0000 13.750 1.4915 0.02991 0.02426 0.0085 0.2828 1.0000 14.000 1.5005 0.03052 0.02485 0.0098 0.2765 1.0000 14.250 1.4903 0.03246 0.02697 0.0119 0.2697 1.0000 14.500 1.4935 0.03368 0.02820 0.0130 0.2628 1.0000 14.750 1.4827 0.03619 0.03086 0.0142 0.2556 1.0000 15.000 1.4858 0.03768 0.03231 0.0149 0.2481 1.0000 15.250 1.4693 0.04114 0.03595 0.0154 0.2405 1.0000 15.500 1.4682 0.04325 0.03804 0.0158 0.2326 1.0000 15.750 1.4526 0.04703 0.04194 0.0157 0.2247 1.0000 16.000 1.4441 0.05019 0.04512 0.0156 0.2166 1.0000 16.250 1.4362 0.05341 0.04835 0.0154 0.2085 1.0000 16.500 1.4212 0.05770 0.05274 0.0147 0.2007 1.0000 16.750 1.4171 0.06064 0.05562 0.0143 0.1924 1.0000 17.000 1.3999 0.06555 0.06064 0.0131 0.1846 1.0000 17.250 1.3926 0.06919 0.06427 0.0123 0.1769 1.0000 17.500 1.3831 0.07322 0.06831 0.0113 0.1690 1.0000 17.750 1.3710 0.07777 0.07293 0.0099 0.1617 1.0000 18.000 1.3701 0.08067 0.07573 0.0092 0.1542 1.0000 18.250 1.3527 0.08628 0.08150 0.0072 0.1472 1.0000 18.500 1.3508 0.08945 0.08461 0.0063 0.1402 1.0000 18.750 1.3373 0.09467 0.08995 0.0043 0.1337 1.0000 19.000 1.3350 0.09802 0.09324 0.0031 0.1271 1.0000