XFOIL Version 6.96 Calculated polar for: AH 80-129 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.2684 0.13101 0.12775 -0.0546 0.7935 0.0039 -12.500 -0.2597 0.12832 0.12507 -0.0565 0.7920 0.0082 -12.250 -0.2560 0.12381 0.12056 -0.0582 0.7906 0.0046 -10.000 -0.1283 0.06901 0.06597 -0.0784 0.7655 0.0068 -9.750 -0.1299 0.06479 0.06177 -0.0798 0.7640 0.0067 -9.500 -0.1282 0.06153 0.05853 -0.0810 0.7622 0.0079 -9.250 -0.1462 0.05310 0.05014 -0.0834 0.7610 0.0058 -9.000 -0.1574 0.04807 0.04515 -0.0856 0.7589 0.0062 -8.750 -0.2166 0.06517 0.06203 -0.0934 0.7650 0.0053 -8.500 -0.2280 0.05933 0.05621 -0.0990 0.7622 0.0053 -8.250 -0.2401 0.05527 0.05211 -0.0995 0.7594 0.0053 -8.000 -0.2489 0.05086 0.04761 -0.0996 0.7568 0.0051 -7.750 -0.2529 0.04703 0.04365 -0.0988 0.7544 0.0049 -7.250 -0.2718 0.03391 0.02995 -0.0929 0.7498 0.0056 -6.750 -0.2755 0.02448 0.01953 -0.0852 0.7447 0.0061 -6.500 -0.2550 0.02438 0.01942 -0.0848 0.7423 0.0069 -6.250 -0.2429 0.02159 0.01620 -0.0822 0.7404 0.0068 -6.000 -0.2244 0.02010 0.01442 -0.0808 0.7387 0.0070 -5.750 -0.2051 0.01850 0.01255 -0.0793 0.7364 0.0072 -5.500 -0.1844 0.01696 0.01074 -0.0780 0.7339 0.0072 -5.250 -0.1620 0.01574 0.00929 -0.0770 0.7313 0.0071 -5.000 -0.1390 0.01470 0.00803 -0.0761 0.7290 0.0072 -4.750 -0.1158 0.01385 0.00703 -0.0752 0.7269 0.0074 -4.250 -0.0691 0.01261 0.00559 -0.0736 0.7223 0.0079 -4.000 -0.0455 0.01212 0.00502 -0.0728 0.7197 0.0085 -3.750 -0.0217 0.01168 0.00451 -0.0721 0.7171 0.0087 -3.500 0.0030 0.01137 0.00410 -0.0715 0.7147 0.0098 -3.250 0.0278 0.01108 0.00371 -0.0710 0.7126 0.0098 -3.000 0.0522 0.01075 0.00332 -0.0704 0.7102 0.0119 -2.750 0.0772 0.01053 0.00310 -0.0699 0.7075 0.0146 -2.500 0.1026 0.01034 0.00287 -0.0695 0.7046 0.0184 -2.250 0.1268 0.01004 0.00268 -0.0689 0.7020 0.0479 -2.000 0.1517 0.00981 0.00250 -0.0685 0.6995 0.0753 -1.750 0.1761 0.00957 0.00237 -0.0680 0.6970 0.1164 -1.500 0.1972 0.00910 0.00228 -0.0671 0.6938 0.2230 -1.250 0.2155 0.00849 0.00219 -0.0656 0.6906 0.3819 -1.000 0.2344 0.00803 0.00209 -0.0640 0.6878 0.5049 -0.750 0.2501 0.00755 0.00200 -0.0616 0.6852 0.6378 -0.500 0.2654 0.00713 0.00205 -0.0588 0.6821 0.7767 -0.250 0.2932 0.00699 0.00211 -0.0587 0.6789 0.8508 0.000 0.3310 0.00697 0.00217 -0.0608 0.6758 0.9016 0.250 0.3703 0.00701 0.00218 -0.0633 0.6728 0.9243 0.500 0.4100 0.00708 0.00221 -0.0660 0.6700 0.9395 0.750 0.4539 0.00716 0.00228 -0.0697 0.6666 0.9488 1.000 0.4877 0.00722 0.00232 -0.0711 0.6630 0.9564 1.250 0.5248 0.00728 0.00233 -0.0734 0.6596 0.9591 1.500 0.5583 0.00734 0.00235 -0.0749 0.6564 0.9619 1.750 0.5894 0.00738 0.00241 -0.0758 0.6522 0.9653 2.000 0.6178 0.00743 0.00244 -0.0762 0.6485 0.9693 2.250 0.6515 0.00749 0.00247 -0.0778 0.6448 0.9709 2.500 0.6843 0.00754 0.00253 -0.0792 0.6406 0.9728 2.750 0.7162 0.00760 0.00261 -0.0804 0.6357 0.9752 3.000 0.7466 0.00766 0.00266 -0.0812 0.6312 0.9781 3.250 0.7752 0.00773 0.00275 -0.0817 0.6263 0.9815 3.500 0.8080 0.00779 0.00283 -0.0832 0.6211 0.9831 3.750 0.8398 0.00786 0.00290 -0.0844 0.6168 0.9851 4.000 0.8710 0.00793 0.00305 -0.0855 0.6118 0.9875 4.250 0.9009 0.00802 0.00317 -0.0863 0.6059 0.9904 4.500 0.9330 0.00810 0.00329 -0.0876 0.6001 0.9920 4.750 0.9645 0.00819 0.00343 -0.0888 0.5942 0.9941 5.000 0.9954 0.00830 0.00360 -0.0899 0.5884 0.9963 5.250 1.0259 0.00844 0.00377 -0.0909 0.5768 0.9991 5.500 1.0399 0.00887 0.00396 -0.0886 0.5233 1.0000 5.750 1.0448 0.00947 0.00432 -0.0845 0.4724 1.0000 6.000 1.0270 0.01087 0.00514 -0.0764 0.3732 1.0000 6.250 1.0160 0.01205 0.00595 -0.0697 0.3052 1.0000 6.500 1.0071 0.01305 0.00670 -0.0635 0.2561 1.0000 6.750 0.9892 0.01468 0.00795 -0.0567 0.1842 1.0000 7.000 0.9811 0.01645 0.00935 -0.0523 0.1156 1.0000 7.250 0.9783 0.01816 0.01076 -0.0489 0.0576 1.0000 7.500 0.9786 0.01980 0.01217 -0.0460 0.0147 1.0000 7.750 0.9882 0.02092 0.01327 -0.0443 0.0064 1.0000 8.000 1.0032 0.02171 0.01416 -0.0432 0.0063 1.0000 8.250 1.0154 0.02271 0.01524 -0.0417 0.0055 1.0000 8.500 1.0283 0.02368 0.01627 -0.0405 0.0051 1.0000 8.750 1.0390 0.02482 0.01750 -0.0390 0.0046 1.0000 9.000 1.0501 0.02594 0.01870 -0.0377 0.0044 1.0000 9.250 1.0590 0.02727 0.02011 -0.0361 0.0041 1.0000 9.500 1.0695 0.02847 0.02137 -0.0349 0.0040 1.0000 9.750 1.0802 0.02968 0.02264 -0.0337 0.0038 1.0000 10.000 1.0894 0.03101 0.02404 -0.0324 0.0037 1.0000 10.250 1.0973 0.03247 0.02558 -0.0312 0.0033 1.0000 10.500 1.1025 0.03418 0.02737 -0.0296 0.0029 1.0000 10.750 1.1121 0.03558 0.02885 -0.0285 0.0024 1.0000 11.000 1.1174 0.03738 0.03074 -0.0271 0.0026 1.0000 11.250 1.1235 0.03915 0.03261 -0.0258 0.0024 1.0000 11.500 1.1273 0.04114 0.03469 -0.0243 0.0027 1.0000 11.750 1.1335 0.04298 0.03663 -0.0229 0.0024 1.0000 12.000 1.1404 0.04476 0.03853 -0.0217 0.0024 1.0000 12.250 1.1472 0.04659 0.04047 -0.0204 0.0024 1.0000 12.500 1.1551 0.04837 0.04237 -0.0192 0.0021 1.0000 12.750 1.1624 0.05027 0.04439 -0.0180 0.0019 1.0000 13.000 1.1707 0.05208 0.04634 -0.0170 0.0021 1.0000 13.250 1.1776 0.05410 0.04849 -0.0160 0.0020 1.0000 13.500 1.1822 0.05648 0.05106 -0.0146 0.0021 1.0000 13.750 1.1854 0.05913 0.05394 -0.0134 0.0021 1.0000 14.000 1.1878 0.06179 0.05677 -0.0128 0.0020 1.0000 14.250 1.1866 0.06503 0.06022 -0.0119 0.0020 1.0000 14.500 1.1818 0.06882 0.06424 -0.0111 0.0021 1.0000 14.750 1.1718 0.07348 0.06916 -0.0105 0.0020 1.0000 15.000 1.1594 0.07856 0.07449 -0.0104 0.0020 1.0000 15.250 1.1506 0.08311 0.07923 -0.0108 0.0021 1.0000 15.500 1.1362 0.08877 0.08510 -0.0117 0.0021 1.0000 15.750 1.1264 0.09381 0.09029 -0.0130 0.0021 1.0000 16.000 1.1023 0.10172 0.09847 -0.0150 0.0021 1.0000 16.250 1.0810 0.10949 0.10645 -0.0178 0.0021 1.0000 16.500 1.0648 0.11670 0.11381 -0.0209 0.0021 1.0000