XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0413MOD 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.4839 0.09284 0.08734 -0.0417 1.0000 0.0392 -10.750 -0.4951 0.08530 0.07986 -0.0463 1.0000 0.0387 -10.500 -0.5322 0.07194 0.06645 -0.0566 1.0000 0.0375 -10.250 -0.5781 0.06356 0.05792 -0.0612 1.0000 0.0367 -10.000 -0.6130 0.05879 0.05300 -0.0609 1.0000 0.0363 -9.750 -0.6304 0.05511 0.04912 -0.0599 1.0000 0.0363 -9.500 -0.6386 0.05210 0.04593 -0.0585 1.0000 0.0364 -9.250 -0.6418 0.04941 0.04304 -0.0569 1.0000 0.0367 -9.000 -0.6417 0.04680 0.04021 -0.0554 1.0000 0.0370 -8.750 -0.6385 0.04423 0.03739 -0.0539 1.0000 0.0373 -8.500 -0.6320 0.04169 0.03456 -0.0527 1.0000 0.0375 -8.250 -0.6223 0.03920 0.03175 -0.0517 1.0000 0.0377 -8.000 -0.5942 0.03624 0.02835 -0.0539 0.9962 0.0379 -7.750 -0.5619 0.03368 0.02539 -0.0564 0.9920 0.0382 -7.500 -0.5295 0.03153 0.02290 -0.0584 0.9873 0.0387 -7.250 -0.4954 0.02966 0.02074 -0.0604 0.9835 0.0393 -7.000 -0.4630 0.02808 0.01890 -0.0619 0.9787 0.0400 -6.750 -0.4297 0.02673 0.01733 -0.0633 0.9740 0.0410 -6.500 -0.3947 0.02554 0.01610 -0.0653 0.9703 0.0427 -6.250 -0.3634 0.02463 0.01517 -0.0666 0.9645 0.0446 -6.000 -0.3296 0.02368 0.01416 -0.0681 0.9597 0.0465 -5.750 -0.2932 0.02272 0.01313 -0.0700 0.9561 0.0485 -5.500 -0.2618 0.02184 0.01223 -0.0712 0.9499 0.0506 -5.250 -0.2268 0.02105 0.01147 -0.0732 0.9448 0.0543 -5.000 -0.1892 0.02031 0.01069 -0.0755 0.9410 0.0605 -4.750 -0.1575 0.01964 0.01001 -0.0767 0.9340 0.0684 -4.500 -0.1223 0.01885 0.00933 -0.0787 0.9286 0.0857 -4.250 -0.0844 0.01781 0.00869 -0.0814 0.9247 0.1492 -4.000 -0.0525 0.01662 0.00825 -0.0836 0.9174 0.3007 -3.750 -0.0206 0.01564 0.00840 -0.0847 0.9119 0.5258 -3.500 0.0065 0.01583 0.00884 -0.0835 0.9053 0.6213 -3.250 0.0341 0.01612 0.00913 -0.0826 0.8972 0.6705 -3.000 0.0637 0.01640 0.00935 -0.0818 0.8915 0.7017 -2.750 0.0866 0.01670 0.00960 -0.0799 0.8818 0.7222 -2.500 0.1151 0.01686 0.00968 -0.0791 0.8758 0.7386 -2.250 0.1392 0.01701 0.00977 -0.0778 0.8658 0.7515 -2.000 0.1705 0.01702 0.00966 -0.0779 0.8595 0.7640 -1.750 0.1919 0.01714 0.00976 -0.0760 0.8492 0.7727 -1.500 0.2242 0.01706 0.00956 -0.0766 0.8426 0.7816 -1.250 0.2482 0.01709 0.00955 -0.0755 0.8322 0.7872 -1.000 0.2796 0.01701 0.00939 -0.0760 0.8249 0.7950 -0.750 0.3043 0.01704 0.00938 -0.0750 0.8150 0.8011 -0.500 0.3325 0.01700 0.00929 -0.0748 0.8072 0.8079 -0.250 0.3611 0.01699 0.00925 -0.0750 0.7977 0.8144 0.000 0.3871 0.01696 0.00919 -0.0742 0.7888 0.8194 0.250 0.4158 0.01692 0.00911 -0.0743 0.7793 0.8254 0.500 0.4435 0.01691 0.00908 -0.0742 0.7686 0.8309 0.750 0.4698 0.01682 0.00896 -0.0734 0.7578 0.8358 1.000 0.4982 0.01676 0.00886 -0.0733 0.7452 0.8412 1.250 0.5263 0.01672 0.00880 -0.0732 0.7309 0.8461 1.500 0.5515 0.01667 0.00874 -0.0724 0.7166 0.8503 1.750 0.5788 0.01664 0.00869 -0.0721 0.7024 0.8553 2.000 0.6084 0.01664 0.00868 -0.0725 0.6878 0.8604 2.250 0.6332 0.01660 0.00864 -0.0715 0.6725 0.8647 2.500 0.6593 0.01658 0.00859 -0.0709 0.6535 0.8697 2.750 0.6874 0.01660 0.00856 -0.0709 0.6322 0.8751 3.000 0.7117 0.01660 0.00853 -0.0699 0.6105 0.8796 3.250 0.7371 0.01666 0.00856 -0.0693 0.5882 0.8846 3.500 0.7642 0.01678 0.00862 -0.0691 0.5644 0.8900 3.750 0.7875 0.01688 0.00869 -0.0681 0.5386 0.8950 4.000 0.8118 0.01705 0.00878 -0.0673 0.5109 0.9006 4.250 0.8367 0.01730 0.00894 -0.0669 0.4801 0.9061 4.500 0.8581 0.01755 0.00908 -0.0656 0.4492 0.9120 4.750 0.8808 0.01793 0.00932 -0.0648 0.4156 0.9186 5.000 0.9011 0.01831 0.00959 -0.0636 0.3819 0.9253 5.250 0.9224 0.01878 0.00994 -0.0626 0.3476 0.9325 5.500 0.9413 0.01926 0.01028 -0.0613 0.3156 0.9407 5.750 0.9606 0.01980 0.01069 -0.0601 0.2871 0.9503 6.000 0.9805 0.02036 0.01117 -0.0591 0.2624 0.9619 6.250 1.0023 0.02098 0.01170 -0.0587 0.2409 0.9797 6.500 1.0263 0.02167 0.01234 -0.0587 0.2219 1.0000 6.750 1.0504 0.02246 0.01310 -0.0588 0.2065 1.0000 7.000 1.0738 0.02329 0.01388 -0.0589 0.1935 1.0000 7.250 1.0969 0.02412 0.01469 -0.0588 0.1822 1.0000 7.500 1.1203 0.02492 0.01552 -0.0588 0.1725 1.0000 7.750 1.1416 0.02584 0.01640 -0.0585 0.1651 1.0000 8.000 1.1646 0.02666 0.01732 -0.0583 0.1580 1.0000 8.250 1.1849 0.02763 0.01826 -0.0578 0.1521 1.0000 8.500 1.2064 0.02854 0.01926 -0.0574 0.1463 1.0000 8.750 1.2266 0.02948 0.02026 -0.0569 0.1407 1.0000 9.000 1.2450 0.03058 0.02128 -0.0562 0.1363 1.0000 9.250 1.2652 0.03154 0.02242 -0.0555 0.1320 1.0000 9.500 1.2834 0.03256 0.02355 -0.0546 0.1276 1.0000 9.750 1.2991 0.03365 0.02463 -0.0536 0.1231 1.0000 10.000 1.3144 0.03474 0.02588 -0.0525 0.1180 1.0000 10.250 1.3275 0.03582 0.02707 -0.0513 0.1127 1.0000 10.750 1.3523 0.03831 0.02978 -0.0490 0.1041 1.0000 11.000 1.3635 0.03963 0.03125 -0.0478 0.0999 1.0000 11.250 1.3728 0.04104 0.03271 -0.0466 0.0965 1.0000 11.500 1.3822 0.04262 0.03443 -0.0455 0.0929 1.0000 11.750 1.3906 0.04427 0.03630 -0.0444 0.0890 1.0000 12.000 1.3969 0.04601 0.03817 -0.0434 0.0856 1.0000 12.250 1.4018 0.04792 0.04007 -0.0425 0.0829 1.0000 12.500 1.4067 0.05010 0.04256 -0.0417 0.0793 1.0000 12.750 1.4097 0.05238 0.04501 -0.0409 0.0760 1.0000 13.000 1.4111 0.05478 0.04751 -0.0404 0.0733 1.0000 13.250 1.4113 0.05746 0.05028 -0.0400 0.0708 1.0000 13.500 1.4099 0.06055 0.05365 -0.0398 0.0678 1.0000 13.750 1.4072 0.06377 0.05706 -0.0398 0.0652 1.0000 14.000 1.4039 0.06709 0.06049 -0.0400 0.0632 1.0000 14.250 1.4002 0.07051 0.06397 -0.0404 0.0616 1.0000 14.500 1.3923 0.07482 0.06852 -0.0411 0.0598 1.0000 14.750 1.3823 0.07960 0.07356 -0.0422 0.0581 1.0000 15.000 1.3716 0.08465 0.07882 -0.0438 0.0565 1.0000 15.250 1.3607 0.08990 0.08424 -0.0458 0.0552 1.0000 15.500 1.3502 0.09527 0.08974 -0.0480 0.0540 1.0000 15.750 1.3405 0.10063 0.09520 -0.0505 0.0530 1.0000 16.000 1.3318 0.10590 0.10053 -0.0529 0.0520 1.0000 16.250 1.3066 0.11492 0.10986 -0.0580 0.0514 1.0000 16.500 1.2756 0.12573 0.12094 -0.0645 0.0509 1.0000 16.750 1.2255 0.14191 0.13742 -0.0751 0.0509 1.0000