XFOIL Version 6.96 Calculated polar for: WORTMANN FX 75-141 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.1815 0.10521 0.10182 -0.0746 0.9620 0.0683 -11.500 -0.1774 0.10081 0.09741 -0.0780 0.9599 0.0714 -11.250 -0.3327 0.10966 0.10623 -0.0629 0.9781 0.0645 -11.000 -0.3123 0.10727 0.10381 -0.0640 0.9731 0.0668 -10.750 -0.3004 0.10310 0.09962 -0.0679 0.9689 0.0693 -10.500 -0.3241 0.09214 0.08871 -0.0856 0.9619 0.0743 -10.250 -0.3136 0.08641 0.08297 -0.0876 0.9593 0.0756 -10.000 -0.2882 0.08459 0.08111 -0.0873 0.9572 0.0770 -9.750 -0.4269 0.04414 0.03934 -0.1288 0.9394 0.0432 -9.500 -0.4244 0.04011 0.03501 -0.1297 0.9329 0.0429 -9.250 -0.4161 0.03642 0.03089 -0.1308 0.9281 0.0429 -9.000 -0.4009 0.03343 0.02741 -0.1319 0.9245 0.0432 -8.750 -0.3924 0.03058 0.02425 -0.1310 0.9198 0.0443 -8.500 -0.3729 0.02932 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1.0593 0.01396 0.00864 -0.0973 0.6272 0.9176 6.250 1.0831 0.01377 0.00847 -0.0962 0.6117 0.9266 6.500 1.1071 0.01366 0.00833 -0.0952 0.5926 0.9376 6.750 1.1321 0.01371 0.00843 -0.0948 0.5709 0.9543 7.000 1.1611 0.01386 0.00855 -0.0952 0.5486 1.0000 7.250 1.1820 0.01417 0.00883 -0.0943 0.5253 1.0000 7.500 1.2009 0.01455 0.00913 -0.0929 0.4993 1.0000 7.750 1.2156 0.01501 0.00953 -0.0909 0.4692 1.0000 8.000 1.2247 0.01558 0.00996 -0.0879 0.4358 1.0000 8.250 1.2288 0.01632 0.01054 -0.0842 0.3958 1.0000 8.500 1.2285 0.01733 0.01132 -0.0801 0.3538 1.0000 8.750 1.2253 0.01862 0.01234 -0.0759 0.3123 1.0000 9.000 1.2230 0.02006 0.01357 -0.0723 0.2752 1.0000 9.250 1.2226 0.02158 0.01489 -0.0693 0.2424 1.0000 9.500 1.2235 0.02316 0.01630 -0.0666 0.2133 1.0000 9.750 1.2248 0.02482 0.01779 -0.0642 0.1865 1.0000 10.000 1.2268 0.02651 0.01934 -0.0620 0.1602 1.0000 10.250 1.2286 0.02830 0.02098 -0.0598 0.1347 1.0000 10.500 1.2284 0.03030 0.02281 -0.0576 0.1143 1.0000 10.750 1.2310 0.03218 0.02460 -0.0557 0.0998 1.0000 11.000 1.2336 0.03408 0.02644 -0.0540 0.0896 1.0000 11.250 1.2398 0.03578 0.02816 -0.0525 0.0815 1.0000 11.500 1.2416 0.03786 0.03017 -0.0507 0.0757 1.0000 11.750 1.2499 0.03945 0.03185 -0.0495 0.0706 1.0000 12.000 1.2544 0.04140 0.03376 -0.0482 0.0664 1.0000 12.250 1.2621 0.04316 0.03559 -0.0469 0.0629 1.0000 12.500 1.2708 0.04485 0.03735 -0.0459 0.0593 1.0000 12.750 1.2782 0.04670 0.03917 -0.0449 0.0562 1.0000 13.000 1.2895 0.04839 0.04089 -0.0438 0.0536 1.0000 13.250 1.2988 0.05011 0.04274 -0.0430 0.0510 1.0000 13.500 1.3087 0.05184 0.04452 -0.0422 0.0487 1.0000 13.750 1.3211 0.05353 0.04617 -0.0414 0.0464 1.0000 14.000 1.3344 0.05535 0.04810 -0.0406 0.0443 1.0000 14.250 1.3424 0.05734 0.05025 -0.0399 0.0426 1.0000 14.500 1.3507 0.05937 0.05240 -0.0392 0.0410 1.0000 14.750 1.3605 0.06136 0.05445 -0.0387 0.0396 1.0000 15.000 1.3814 0.06311 0.05616 -0.0381 0.0378 1.0000 15.250 1.3845 0.06596 0.05923 -0.0375 0.0369 1.0000 15.500 1.3831 0.06895 0.06249 -0.0371 0.0360 1.0000 15.750 1.3822 0.07207 0.06582 -0.0368 0.0351 1.0000 16.000 1.3813 0.07522 0.06915 -0.0367 0.0341 1.0000 16.250 1.3806 0.07851 0.07260 -0.0368 0.0334 1.0000 16.500 1.3788 0.08196 0.07619 -0.0371 0.0327 1.0000 16.750 1.3782 0.08538 0.07973 -0.0374 0.0321 1.0000 17.000 1.3790 0.08888 0.08333 -0.0378 0.0315 1.0000 17.250 1.3748 0.09362 0.08824 -0.0384 0.0309 1.0000 17.500 1.3588 0.09944 0.09430 -0.0400 0.0307 1.0000 17.750 1.3399 0.10551 0.10064 -0.0423 0.0306 1.0000 18.000 1.3200 0.11208 0.10746 -0.0452 0.0305 1.0000 18.250 1.2991 0.11922 0.11484 -0.0488 0.0305 1.0000 18.500 1.2770 0.12699 0.12284 -0.0531 0.0305 1.0000 18.750 1.2533 0.13546 0.13153 -0.0582 0.0306 1.0000 19.000 1.2294 0.14453 0.14079 -0.0639 0.0307 1.0000 19.250 1.2021 0.15507 0.15156 -0.0714 0.0310 1.0000