XFOIL Version 6.96 Calculated polar for: GOE 553 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 ------ -------- --------- --------- -------- -------- -------- -12.500 -0.3046 0.13013 0.12765 -0.0311 1.0000 0.0284 -12.250 -0.3212 0.12330 0.12083 -0.0370 1.0000 0.0300 -12.000 -0.3166 0.11961 0.11716 -0.0372 1.0000 0.0302 -11.750 -0.3056 0.11763 0.11519 -0.0366 1.0000 0.0305 -11.500 -0.2965 0.11540 0.11297 -0.0364 1.0000 0.0308 -11.250 -0.2897 0.11294 0.11053 -0.0367 1.0000 0.0312 -11.000 -0.2848 0.11021 0.10783 -0.0372 1.0000 0.0316 -10.750 -0.2308 0.09534 0.09321 -0.0453 1.0000 0.0349 -10.500 -0.2241 0.09328 0.09118 -0.0439 1.0000 0.0352 -10.250 -0.2083 0.09072 0.08862 -0.0448 0.9983 0.0356 -10.000 -0.1916 0.08733 0.08523 -0.0473 0.9911 0.0361 -9.750 -0.1773 0.08335 0.08125 -0.0505 0.9820 0.0369 -9.500 -0.1656 0.07833 0.07622 -0.0549 0.9705 0.0383 -9.000 -0.2624 0.08264 0.08047 -0.0494 0.9903 0.0374 -8.750 -0.2935 0.06126 0.05907 -0.0769 0.9643 0.0406 -8.500 -0.2578 0.06111 0.05892 -0.0783 0.9524 0.0410 -8.250 -0.2186 0.05611 0.05385 -0.0898 0.9303 0.0417 -8.000 -0.1991 0.04809 0.04551 -0.1045 0.8850 0.0427 -7.750 -0.2362 0.03748 0.03382 -0.1104 0.8337 0.0471 -7.500 -0.2178 0.03587 0.03213 -0.1098 0.7984 0.0475 -7.250 -0.2006 0.03459 0.03069 -0.1091 0.7682 0.0481 -7.000 -0.1826 0.03324 0.02918 -0.1087 0.7450 0.0488 -6.750 -0.1644 0.03166 0.02738 -0.1084 0.7274 0.0501 -6.500 -0.1515 0.02831 0.02336 -0.1084 0.7143 0.0549 -6.250 -0.1370 0.02113 0.01496 -0.1071 0.7044 0.0404 -6.000 -0.1123 0.01982 0.01349 -0.1067 0.6942 0.0400 -5.750 -0.0876 0.01844 0.01191 -0.1063 0.6849 0.0399 -5.500 -0.0619 0.01751 0.01078 -0.1060 0.6766 0.0400 -5.250 -0.0357 0.01680 0.00990 -0.1056 0.6685 0.0402 -5.000 -0.0102 0.01558 0.00853 -0.1052 0.6615 0.0407 -4.750 0.0161 0.01472 0.00765 -0.1050 0.6545 0.0413 -4.500 0.0426 0.01417 0.00702 -0.1046 0.6479 0.0418 -4.250 0.0694 0.01367 0.00648 -0.1043 0.6419 0.0423 -4.000 0.0964 0.01323 0.00601 -0.1040 0.6357 0.0428 -3.750 0.1233 0.01287 0.00558 -0.1037 0.6299 0.0434 -3.500 0.1504 0.01252 0.00520 -0.1034 0.6242 0.0441 -3.250 0.1776 0.01219 0.00485 -0.1032 0.6183 0.0449 -3.000 0.2050 0.01199 0.00457 -0.1029 0.6129 0.0459 -2.750 0.2322 0.01172 0.00427 -0.1026 0.6076 0.0468 -2.500 0.2591 0.01129 0.00385 -0.1024 0.6018 0.0482 -2.250 0.2864 0.01107 0.00360 -0.1022 0.5959 0.0497 -2.000 0.3140 0.01091 0.00340 -0.1020 0.5904 0.0514 -1.750 0.3420 0.01074 0.00322 -0.1018 0.5846 0.0533 -1.500 0.3696 0.01054 0.00299 -0.1016 0.5788 0.0566 -1.250 0.3973 0.01044 0.00285 -0.1014 0.5732 0.0619 -1.000 0.4249 0.01014 0.00273 -0.1013 0.5668 0.0961 -0.750 0.4501 0.00926 0.00257 -0.1013 0.5605 0.3314 -0.500 0.4762 0.00892 0.00265 -0.1011 0.5543 0.4862 -0.250 0.5036 0.00885 0.00270 -0.1008 0.5472 0.5361 0.000 0.5306 0.00889 0.00272 -0.1004 0.5399 0.5659 0.250 0.5582 0.00886 0.00275 -0.1001 0.5314 0.5898 0.500 0.5852 0.00892 0.00276 -0.0998 0.5232 0.6113 0.750 0.6126 0.00891 0.00280 -0.0995 0.5144 0.6322 1.000 0.6390 0.00895 0.00285 -0.0990 0.5065 0.6578 1.250 0.6662 0.00896 0.00291 -0.0987 0.4977 0.6801 1.500 0.6927 0.00902 0.00295 -0.0982 0.4893 0.6965 1.750 0.7198 0.00904 0.00300 -0.0979 0.4805 0.7118 2.000 0.7461 0.00910 0.00305 -0.0975 0.4723 0.7294 2.250 0.7726 0.00913 0.00312 -0.0971 0.4631 0.7506 2.500 0.7979 0.00915 0.00320 -0.0965 0.4543 0.7797 2.750 0.8216 0.00908 0.00327 -0.0954 0.4455 0.8315 3.000 0.8598 0.00897 0.00334 -0.0975 0.4365 1.0000 3.250 0.8867 0.00914 0.00343 -0.0973 0.4283 1.0000 3.500 0.9135 0.00932 0.00355 -0.0971 0.4210 1.0000 3.750 0.9403 0.00948 0.00367 -0.0969 0.4138 1.0000 4.000 0.9664 0.00969 0.00381 -0.0965 0.4072 1.0000 4.250 0.9933 0.00984 0.00395 -0.0963 0.4004 1.0000 4.500 1.0191 0.01005 0.00410 -0.0959 0.3938 1.0000 4.750 1.0455 0.01022 0.00426 -0.0957 0.3878 1.0000 5.000 1.0717 0.01041 0.00443 -0.0953 0.3814 1.0000 5.250 1.0967 0.01066 0.00462 -0.0949 0.3754 1.0000 5.500 1.1234 0.01080 0.00479 -0.0946 0.3703 1.0000 5.750 1.1490 0.01100 0.00498 -0.0943 0.3648 1.0000 6.000 1.1737 0.01127 0.00520 -0.0937 0.3595 1.0000 6.250 1.1999 0.01143 0.00540 -0.0934 0.3547 1.0000 6.500 1.2252 0.01163 0.00561 -0.0930 0.3493 1.0000 6.750 1.2492 0.01191 0.00585 -0.0924 0.3438 1.0000 7.000 1.2746 0.01208 0.00606 -0.0920 0.3374 1.0000 7.250 1.2983 0.01233 0.00629 -0.0914 0.3301 1.0000 7.500 1.3224 0.01256 0.00654 -0.0908 0.3234 1.0000 7.750 1.3462 0.01280 0.00678 -0.0902 0.3161 1.0000 8.000 1.3689 0.01309 0.00706 -0.0894 0.3097 1.0000 8.250 1.3925 0.01332 0.00733 -0.0887 0.3020 1.0000 8.500 1.4140 0.01364 0.00763 -0.0877 0.2938 1.0000 8.750 1.4360 0.01393 0.00793 -0.0869 0.2841 1.0000 9.000 1.4569 0.01425 0.00826 -0.0858 0.2743 1.0000 9.250 1.4759 0.01466 0.00863 -0.0845 0.2636 1.0000 9.500 1.4946 0.01505 0.00902 -0.0831 0.2518 1.0000 9.750 1.5114 0.01548 0.00944 -0.0814 0.2398 1.0000 10.000 1.5248 0.01599 0.00992 -0.0792 0.2276 1.0000 10.250 1.5366 0.01657 0.01046 -0.0767 0.2166 1.0000 10.750 1.5589 0.01785 0.01170 -0.0720 0.1984 1.0000 11.000 1.5673 0.01865 0.01248 -0.0694 0.1902 1.0000 11.250 1.5766 0.01945 0.01328 -0.0672 0.1829 1.0000 11.500 1.5839 0.02039 0.01422 -0.0648 0.1765 1.0000 11.750 1.5939 0.02125 0.01512 -0.0628 0.1708 1.0000 12.000 1.5994 0.02240 0.01629 -0.0606 0.1656 1.0000 12.250 1.6090 0.02339 0.01734 -0.0590 0.1607 1.0000 12.500 1.6161 0.02461 0.01860 -0.0573 0.1548 1.0000 12.750 1.6192 0.02617 0.02018 -0.0555 0.1492 1.0000 13.000 1.6286 0.02740 0.02147 -0.0544 0.1412 1.0000 13.250 1.6321 0.02913 0.02323 -0.0531 0.1316 1.0000 13.750 1.6130 0.03536 0.02924 -0.0504 0.0883 1.0000 14.000 1.6001 0.03912 0.03297 -0.0496 0.0792 1.0000 14.250 1.5916 0.04258 0.03647 -0.0490 0.0743 1.0000 14.500 1.5811 0.04637 0.04031 -0.0487 0.0705 1.0000 14.750 1.5771 0.04954 0.04358 -0.0485 0.0678 1.0000 15.000 1.5703 0.05314 0.04726 -0.0485 0.0651 1.0000 15.250 1.5603 0.05724 0.05142 -0.0488 0.0628 1.0000 15.500 1.5494 0.06160 0.05585 -0.0492 0.0607 1.0000 15.750 1.5478 0.06493 0.05929 -0.0496 0.0588 1.0000 16.000 1.5424 0.06881 0.06326 -0.0503 0.0569 1.0000 16.250 1.5342 0.07319 0.06772 -0.0512 0.0550 1.0000 16.500 1.5227 0.07818 0.07277 -0.0523 0.0532 1.0000 16.750 1.5169 0.08244 0.07713 -0.0534 0.0517 1.0000 17.000 1.5149 0.08621 0.08100 -0.0544 0.0498 1.0000 17.250 1.5085 0.09071 0.08557 -0.0557 0.0481 1.0000 17.500 1.4989 0.09578 0.09070 -0.0574 0.0464 1.0000