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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.7217 0.07173 0.06788 -0.0994 1.0000 0.0355 -16.000 -0.7483 0.06564 0.06163 -0.1030 1.0000 0.0355 -15.750 -0.7685 0.06090 0.05676 -0.1052 1.0000 0.0355 -15.500 -0.7874 0.05704 0.05279 -0.1065 1.0000 0.0354 -15.250 -0.8020 0.05370 0.04938 -0.1072 0.9993 0.0355 -15.000 -0.7927 0.04973 0.04528 -0.1120 0.9962 0.0357 -14.750 -0.7817 0.04638 0.04184 -0.1160 0.9893 0.0358 -14.500 -0.7681 0.04349 0.03886 -0.1197 0.9837 0.0360 -14.250 -0.7518 0.04074 0.03601 -0.1236 0.9795 0.0362 -14.000 -0.7368 0.03829 0.03348 -0.1268 0.9722 0.0364 -13.750 -0.7158 0.03597 0.03105 -0.1308 0.9677 0.0368 -13.500 -0.6919 0.03374 0.02872 -0.1349 0.9634 0.0370 -13.250 -0.6660 0.03182 0.02671 -0.1389 0.9574 0.0374 -13.000 -0.6366 0.02996 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0.6158 0.00973 0.00342 -0.1044 0.5777 0.4878 1.500 0.6398 0.00976 0.00345 -0.1036 0.5693 0.5028 1.750 0.6635 0.00974 0.00350 -0.1027 0.5596 0.5212 2.000 0.6864 0.00977 0.00355 -0.1017 0.5504 0.5435 2.250 0.7090 0.00977 0.00363 -0.1006 0.5403 0.5703 2.500 0.7307 0.00980 0.00373 -0.0994 0.5307 0.6021 3.000 0.7723 0.00991 0.00394 -0.0965 0.5096 0.6696 3.250 0.7913 0.01001 0.00404 -0.0947 0.4993 0.6994 3.500 0.8108 0.01002 0.00416 -0.0930 0.4901 0.7328 3.750 0.8258 0.01001 0.00432 -0.0903 0.4824 0.7880 4.000 0.8403 0.00997 0.00454 -0.0872 0.4761 0.8991 4.250 0.8875 0.01018 0.00479 -0.0913 0.4689 0.9635 4.500 0.9354 0.01052 0.00503 -0.0957 0.4620 1.0000 4.750 0.9529 0.01064 0.00516 -0.0937 0.4570 1.0000 5.000 0.9703 0.01082 0.00530 -0.0918 0.4517 1.0000 5.250 0.9879 0.01105 0.00546 -0.0899 0.4469 1.0000 5.500 1.0076 0.01128 0.00565 -0.0884 0.4425 1.0000 5.750 1.0278 0.01144 0.00583 -0.0870 0.4385 1.0000 6.000 1.0475 0.01165 0.00603 -0.0856 0.4342 1.0000 6.250 1.0672 0.01190 0.00624 -0.0842 0.4300 1.0000 6.500 1.0887 0.01220 0.00647 -0.0832 0.4256 1.0000 6.750 1.1081 0.01239 0.00670 -0.0817 0.4220 1.0000 7.000 1.1269 0.01261 0.00694 -0.0802 0.4173 1.0000 7.250 1.1453 0.01289 0.00719 -0.0787 0.4123 1.0000 7.500 1.1633 0.01323 0.00748 -0.0772 0.4063 1.0000 7.750 1.1792 0.01347 0.00777 -0.0753 0.4003 1.0000 8.000 1.1951 0.01380 0.00808 -0.0735 0.3940 1.0000 8.250 1.2125 0.01419 0.00843 -0.0719 0.3886 1.0000 8.500 1.2302 0.01447 0.00876 -0.0705 0.3839 1.0000 8.750 1.2472 0.01481 0.00912 -0.0690 0.3784 1.0000 9.000 1.2620 0.01527 0.00954 -0.0672 0.3726 1.0000 9.250 1.2791 0.01564 0.00996 -0.0658 0.3668 1.0000 9.500 1.2950 0.01606 0.01040 -0.0642 0.3606 1.0000 9.750 1.3082 0.01663 0.01093 -0.0624 0.3543 1.0000 10.000 1.3252 0.01706 0.01141 -0.0611 0.3479 1.0000 10.250 1.3397 0.01761 0.01197 -0.0596 0.3411 1.0000 10.500 1.3530 0.01825 0.01260 -0.0579 0.3346 1.0000 10.750 1.3681 0.01882 0.01320 -0.0566 0.3269 1.0000 11.000 1.3784 0.01964 0.01400 -0.0547 0.3191 1.0000 11.250 1.3925 0.02032 0.01470 -0.0534 0.3101 1.0000 11.500 1.4018 0.02126 0.01562 -0.0515 0.3015 1.0000 11.750 1.4123 0.02218 0.01653 -0.0500 0.2913 1.0000 12.000 1.4214 0.02322 0.01756 -0.0483 0.2823 1.0000 12.250 1.4283 0.02442 0.01874 -0.0465 0.2728 1.0000 12.500 1.4377 0.02553 0.01985 -0.0451 0.2637 1.0000 12.750 1.4418 0.02701 0.02129 -0.0433 0.2547 1.0000 13.000 1.4507 0.02823 0.02253 -0.0419 0.2454 1.0000 13.250 1.4548 0.02982 0.02410 -0.0404 0.2364 1.0000 13.500 1.4585 0.03151 0.02577 -0.0389 0.2263 1.0000 13.750 1.4631 0.03320 0.02745 -0.0376 0.2159 1.0000 14.000 1.4643 0.03520 0.02943 -0.0362 0.2062 1.0000 14.250 1.4648 0.03734 0.03155 -0.0349 0.1948 1.0000 14.500 1.4641 0.03965 0.03384 -0.0337 0.1812 1.0000 14.750 1.4595 0.04239 0.03652 -0.0325 0.1663 1.0000 15.000 1.4514 0.04553 0.03960 -0.0314 0.1502 1.0000 15.250 1.4414 0.04896 0.04297 -0.0303 0.1359 1.0000 15.500 1.4317 0.05246 0.04644 -0.0295 0.1253 1.0000 15.750 1.4243 0.05583 0.04979 -0.0289 0.1175 1.0000 16.000 1.4199 0.05897 0.05296 -0.0284 0.1122 1.0000 16.250 1.4135 0.06241 0.05642 -0.0281 0.1072 1.0000 16.500 1.4084 0.06579 0.05983 -0.0279 0.1031 1.0000 16.750 1.4077 0.06871 0.06281 -0.0278 0.1001 1.0000 17.000 1.4031 0.07216 0.06628 -0.0279 0.0972 1.0000 17.250 1.3958 0.07598 0.07013 -0.0280 0.0946 1.0000 17.500 1.3978 0.07874 0.07296 -0.0282 0.0928 1.0000 17.750 1.3983 0.08169 0.07598 -0.0285 0.0910 1.0000 18.000 1.3968 0.08494 0.07928 -0.0288 0.0891 1.0000 18.250 1.3945 0.08830 0.08268 -0.0293 0.0875 1.0000