XFOIL Version 6.96 Calculated polar for: NACA 4418 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.9676 0.08506 0.08148 -0.0813 1.0000 0.0280 -18.750 -1.0014 0.07702 0.07333 -0.0857 1.0000 0.0281 -18.500 -1.0426 0.06836 0.06451 -0.0905 1.0000 0.0281 -18.250 -1.0844 0.05978 0.05577 -0.0951 1.0000 0.0281 -18.000 -1.1206 0.05186 0.04769 -0.0995 1.0000 0.0282 -17.750 -1.1470 0.04529 0.04097 -0.1031 1.0000 0.0282 -17.500 -1.1665 0.04007 0.03563 -0.1056 1.0000 0.0283 -17.250 -1.1824 0.03602 0.03146 -0.1067 1.0000 0.0284 -17.000 -1.1932 0.03282 0.02817 -0.1072 0.9996 0.0286 -16.750 -1.1827 0.03012 0.02536 -0.1101 0.9975 0.0288 -16.500 -1.1688 0.02798 0.02314 -0.1124 0.9953 0.0290 -16.250 -1.1519 0.02626 0.02134 -0.1144 0.9935 0.0293 -16.000 -1.1340 0.02484 0.01984 -0.1158 0.9914 0.0296 -15.750 -1.1173 0.02367 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-0.0962 0.5309 0.2128 -1.250 0.3357 0.00888 0.00218 -0.0962 0.5244 0.2199 -1.000 0.3631 0.00887 0.00218 -0.0960 0.5169 0.2300 -0.750 0.3904 0.00887 0.00220 -0.0958 0.5098 0.2432 -0.500 0.4182 0.00884 0.00221 -0.0958 0.5033 0.2598 -0.250 0.4454 0.00885 0.00224 -0.0956 0.4963 0.2764 0.000 0.4727 0.00886 0.00227 -0.0954 0.4899 0.2925 0.250 0.5003 0.00884 0.00230 -0.0953 0.4836 0.3107 0.500 0.5274 0.00885 0.00234 -0.0951 0.4769 0.3281 1.000 0.5821 0.00888 0.00243 -0.0948 0.4647 0.3578 1.250 0.6090 0.00891 0.00248 -0.0946 0.4582 0.3732 1.500 0.6358 0.00894 0.00254 -0.0944 0.4521 0.3929 1.750 0.6630 0.00892 0.00260 -0.0942 0.4462 0.4207 2.000 0.6894 0.00892 0.00267 -0.0939 0.4397 0.4575 2.250 0.7155 0.00892 0.00276 -0.0936 0.4335 0.4966 2.500 0.7424 0.00891 0.00285 -0.0934 0.4273 0.5320 2.750 0.7683 0.00896 0.00295 -0.0930 0.4198 0.5631 3.000 0.7941 0.00900 0.00305 -0.0927 0.4119 0.5966 3.250 0.8196 0.00907 0.00317 -0.0922 0.4025 0.6271 3.500 0.8449 0.00913 0.00329 -0.0917 0.3950 0.6592 3.750 0.8704 0.00912 0.00342 -0.0913 0.3884 0.7100 4.000 0.8946 0.00916 0.00357 -0.0905 0.3816 0.7616 4.250 0.9193 0.00920 0.00372 -0.0899 0.3756 0.8009 4.500 0.9432 0.00925 0.00387 -0.0890 0.3686 0.8395 4.750 0.9646 0.00934 0.00405 -0.0876 0.3619 0.8856 5.000 0.9853 0.00940 0.00422 -0.0859 0.3563 0.9380 5.250 1.0140 0.00958 0.00440 -0.0861 0.3481 0.9761 5.500 1.0489 0.00980 0.00459 -0.0878 0.3409 0.9974 5.750 1.0714 0.00997 0.00474 -0.0868 0.3339 1.0000 6.000 1.0909 0.01021 0.00493 -0.0853 0.3259 1.0000 6.250 1.1130 0.01040 0.00510 -0.0843 0.3190 1.0000 6.500 1.1330 0.01069 0.00533 -0.0829 0.3094 1.0000 6.750 1.1537 0.01096 0.00556 -0.0817 0.2982 1.0000 7.000 1.1736 0.01129 0.00583 -0.0803 0.2870 1.0000 7.250 1.1932 0.01164 0.00613 -0.0790 0.2761 1.0000 7.500 1.2131 0.01199 0.00643 -0.0778 0.2647 1.0000 7.750 1.2312 0.01243 0.00679 -0.0763 0.2506 1.0000 8.000 1.2476 0.01295 0.00722 -0.0745 0.2346 1.0000 8.250 1.2634 0.01352 0.00769 -0.0728 0.2181 1.0000 8.500 1.2796 0.01408 0.00818 -0.0711 0.2048 1.0000 8.750 1.2964 0.01462 0.00867 -0.0696 0.1948 1.0000 9.000 1.3138 0.01514 0.00915 -0.0682 0.1854 1.0000 9.250 1.3305 0.01570 0.00968 -0.0667 0.1770 1.0000 9.500 1.3458 0.01635 0.01027 -0.0652 0.1679 1.0000 9.750 1.3627 0.01692 0.01083 -0.0638 0.1608 1.0000 10.000 1.3781 0.01759 0.01147 -0.0624 0.1538 1.0000 10.250 1.3941 0.01824 0.01211 -0.0610 0.1474 1.0000 10.500 1.4086 0.01899 0.01283 -0.0596 0.1409 1.0000 10.750 1.4233 0.01974 0.01357 -0.0582 0.1343 1.0000 11.000 1.4369 0.02059 0.01440 -0.0568 0.1279 1.0000 11.250 1.4490 0.02153 0.01532 -0.0552 0.1207 1.0000 11.500 1.4610 0.02251 0.01628 -0.0537 0.1136 1.0000 11.750 1.4712 0.02364 0.01738 -0.0522 0.1065 1.0000 12.000 1.4800 0.02489 0.01861 -0.0506 0.0992 1.0000 12.250 1.4900 0.02609 0.01980 -0.0492 0.0930 1.0000 12.500 1.4987 0.02742 0.02112 -0.0477 0.0877 1.0000 12.750 1.5066 0.02886 0.02256 -0.0464 0.0827 1.0000 13.000 1.5158 0.03026 0.02397 -0.0452 0.0785 1.0000 13.250 1.5224 0.03188 0.02559 -0.0439 0.0743 1.0000 13.500 1.5305 0.03343 0.02717 -0.0428 0.0708 1.0000 13.750 1.5363 0.03523 0.02898 -0.0417 0.0672 1.0000 14.000 1.5438 0.03693 0.03070 -0.0408 0.0641 1.0000 14.250 1.5483 0.03894 0.03273 -0.0399 0.0610 1.0000 14.500 1.5540 0.04087 0.03469 -0.0391 0.0584 1.0000 14.750 1.5580 0.04301 0.03685 -0.0383 0.0556 1.0000 15.000 1.5620 0.04520 0.03908 -0.0376 0.0534 1.0000 15.250 1.5652 0.04752 0.04144 -0.0370 0.0512 1.0000 15.500 1.5669 0.05003 0.04398 -0.0364 0.0493 1.0000 15.750 1.5707 0.05234 0.04634 -0.0360 0.0478 1.0000 16.000 1.5724 0.05493 0.04898 -0.0356 0.0463 1.0000 16.250 1.5727 0.05772 0.05181 -0.0353 0.0449 1.0000 16.500 1.5739 0.06043 0.05457 -0.0350 0.0438 1.0000 16.750 1.5748 0.06320 0.05740 -0.0349 0.0428 1.0000 17.000 1.5744 0.06616 0.06042 -0.0348 0.0419 1.0000 17.250 1.5736 0.06918 0.06349 -0.0347 0.0409 1.0000 17.500 1.5711 0.07245 0.06682 -0.0348 0.0401 1.0000 17.750 1.5689 0.07574 0.07018 -0.0349 0.0394 1.0000 18.000 1.5683 0.07880 0.07330 -0.0351 0.0388 1.0000 18.250 1.5657 0.08215 0.07673 -0.0353 0.0381 1.0000 18.500 1.5625 0.08563 0.08027 -0.0357 0.0375 1.0000 18.750 1.5596 0.08907 0.08377 -0.0361 0.0368 1.0000 19.000 1.5542 0.09289 0.08766 -0.0367 0.0363 1.0000 19.250 1.5492 0.09666 0.09148 -0.0373 0.0357 1.0000