XFOIL Version 6.96 Calculated polar for: GOE 420 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.6574 0.11384 0.11026 -0.0710 1.0000 0.0273 -18.250 -0.6871 0.10496 0.10121 -0.0759 1.0000 0.0273 -18.000 -0.7074 0.09794 0.09404 -0.0799 1.0000 0.0275 -17.750 -0.7207 0.09233 0.08833 -0.0829 1.0000 0.0275 -17.500 -0.7315 0.08729 0.08319 -0.0856 1.0000 0.0276 -17.250 -0.7414 0.08249 0.07828 -0.0881 1.0000 0.0278 -17.000 -0.7481 0.07838 0.07410 -0.0902 1.0000 0.0278 -16.750 -0.7552 0.07428 0.06991 -0.0922 1.0000 0.0279 -16.500 -0.7600 0.07071 0.06626 -0.0938 1.0000 0.0279 -16.250 -0.7662 0.06702 0.06250 -0.0954 1.0000 0.0281 -16.000 -0.7722 0.06360 0.05900 -0.0967 1.0000 0.0282 -15.750 -0.7713 0.05979 0.05511 -0.0993 0.9918 0.0283 -15.500 -0.7645 0.05629 0.05151 -0.1030 0.9820 0.0284 -15.250 -0.7552 0.05291 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0.3396 -0.500 0.4178 0.00987 0.00293 -0.1044 0.5695 0.3472 -0.250 0.4438 0.00989 0.00293 -0.1039 0.5617 0.3552 0.000 0.4687 0.00992 0.00295 -0.1033 0.5540 0.3638 0.250 0.4944 0.00994 0.00297 -0.1028 0.5450 0.3728 0.500 0.5188 0.01001 0.00299 -0.1020 0.5362 0.3797 0.750 0.5440 0.01003 0.00303 -0.1014 0.5269 0.3879 1.000 0.5676 0.01011 0.00307 -0.1006 0.5176 0.3964 1.250 0.5917 0.01016 0.00313 -0.0998 0.5073 0.4059 1.500 0.6145 0.01025 0.00320 -0.0987 0.4972 0.4188 1.750 0.6368 0.01033 0.00328 -0.0976 0.4868 0.4318 2.000 0.6592 0.01043 0.00336 -0.0966 0.4778 0.4428 2.250 0.6812 0.01053 0.00346 -0.0954 0.4697 0.4554 2.500 0.7028 0.01064 0.00357 -0.0942 0.4626 0.4687 2.750 0.7241 0.01074 0.00368 -0.0929 0.4548 0.4829 3.000 0.7414 0.01088 0.00380 -0.0908 0.4468 0.4961 3.250 0.7619 0.01096 0.00391 -0.0894 0.4397 0.5102 3.500 0.7799 0.01109 0.00406 -0.0875 0.4323 0.5274 3.750 0.7988 0.01121 0.00423 -0.0859 0.4267 0.5492 4.000 0.8200 0.01129 0.00440 -0.0846 0.4224 0.5783 4.250 0.8402 0.01138 0.00460 -0.0832 0.4185 0.6121 4.500 0.8597 0.01152 0.00480 -0.0817 0.4146 0.6433 4.750 0.8785 0.01169 0.00502 -0.0800 0.4107 0.6690 5.000 0.8991 0.01180 0.00521 -0.0787 0.4073 0.6935 5.500 0.9356 0.01191 0.00564 -0.0751 0.3998 0.7766 5.750 0.9700 0.01188 0.00597 -0.0764 0.3959 0.9481 6.000 1.0074 0.01216 0.00623 -0.0788 0.3919 1.0000 6.250 1.0284 0.01236 0.00644 -0.0777 0.3891 1.0000 6.500 1.0496 0.01257 0.00666 -0.0767 0.3859 1.0000 6.750 1.0697 0.01281 0.00691 -0.0755 0.3823 1.0000 7.000 1.0882 0.01310 0.00718 -0.0740 0.3778 1.0000 7.250 1.1055 0.01345 0.00750 -0.0725 0.3735 1.0000 7.500 1.1252 0.01372 0.00779 -0.0713 0.3677 1.0000 7.750 1.1420 0.01409 0.00814 -0.0697 0.3600 1.0000 8.000 1.1574 0.01452 0.00853 -0.0680 0.3517 1.0000 8.250 1.1744 0.01492 0.00893 -0.0665 0.3436 1.0000 8.500 1.1893 0.01542 0.00939 -0.0648 0.3368 1.0000 8.750 1.2077 0.01580 0.00979 -0.0637 0.3301 1.0000 9.000 1.2221 0.01636 0.01032 -0.0620 0.3227 1.0000 9.250 1.2381 0.01687 0.01083 -0.0606 0.3141 1.0000 9.500 1.2497 0.01759 0.01151 -0.0587 0.3036 1.0000 9.750 1.2627 0.01829 0.01217 -0.0570 0.2921 1.0000 10.000 1.2730 0.01914 0.01298 -0.0552 0.2802 1.0000 10.250 1.2828 0.02006 0.01385 -0.0533 0.2692 1.0000 10.500 1.2925 0.02102 0.01477 -0.0515 0.2585 1.0000 10.750 1.3037 0.02192 0.01566 -0.0500 0.2500 1.0000 11.000 1.3128 0.02298 0.01669 -0.0483 0.2413 1.0000 11.250 1.3241 0.02394 0.01765 -0.0469 0.2338 1.0000 11.500 1.3328 0.02509 0.01878 -0.0453 0.2258 1.0000 11.750 1.3431 0.02618 0.01987 -0.0440 0.2188 1.0000 12.000 1.3516 0.02743 0.02110 -0.0425 0.2111 1.0000 12.250 1.3604 0.02869 0.02237 -0.0412 0.2039 1.0000 12.500 1.3683 0.03005 0.02372 -0.0400 0.1958 1.0000 12.750 1.3755 0.03151 0.02518 -0.0387 0.1875 1.0000 13.000 1.3792 0.03329 0.02693 -0.0374 0.1767 1.0000 13.250 1.3808 0.03529 0.02889 -0.0360 0.1629 1.0000 13.500 1.3775 0.03776 0.03128 -0.0346 0.1454 1.0000 13.750 1.3726 0.04046 0.03391 -0.0332 0.1303 1.0000 14.000 1.3699 0.04308 0.03649 -0.0321 0.1196 1.0000 14.250 1.3674 0.04573 0.03913 -0.0312 0.1111 1.0000 14.500 1.3653 0.04844 0.04183 -0.0303 0.1038 1.0000 14.750 1.3684 0.05069 0.04412 -0.0298 0.0996 1.0000 15.000 1.3687 0.05328 0.04673 -0.0292 0.0950 1.0000 15.250 1.3695 0.05586 0.04934 -0.0288 0.0919 1.0000 15.500 1.3725 0.05825 0.05177 -0.0285 0.0888 1.0000 15.750 1.3735 0.06091 0.05447 -0.0282 0.0862 1.0000 16.000 1.3726 0.06382 0.05742 -0.0280 0.0835 1.0000 16.250 1.3744 0.06646 0.06012 -0.0279 0.0813 1.0000 16.500 1.3757 0.06921 0.06292 -0.0279 0.0792 1.0000 16.750 1.3764 0.07206 0.06582 -0.0280 0.0773 1.0000 17.000 1.3745 0.07528 0.06909 -0.0281 0.0755 1.0000 17.250 1.3742 0.07836 0.07222 -0.0284 0.0739 1.0000 17.500 1.3762 0.08116 0.07508 -0.0286 0.0724 1.0000 17.750 1.3764 0.08421 0.07820 -0.0290 0.0710 1.0000 18.000 1.3766 0.08729 0.08134 -0.0294 0.0695 1.0000 18.250 1.3742 0.09076 0.08486 -0.0300 0.0681 1.0000