XFOIL Version 6.96 Calculated polar for: GOE 534 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 ------ -------- --------- --------- -------- -------- -------- -15.250 -0.6662 0.09539 0.09208 -0.0435 1.0000 0.0274 -15.000 -0.7080 0.08432 0.08082 -0.0507 1.0000 0.0277 -14.750 -0.7330 0.07660 0.07297 -0.0558 1.0000 0.0278 -14.500 -0.7516 0.07022 0.06648 -0.0600 1.0000 0.0279 -14.250 -0.7700 0.06420 0.06037 -0.0641 1.0000 0.0280 -14.000 -0.7834 0.05950 0.05561 -0.0670 1.0000 0.0281 -13.750 -0.7977 0.05502 0.05111 -0.0696 1.0000 0.0283 -13.500 -0.8188 0.05003 0.04606 -0.0724 1.0000 0.0283 -13.250 -0.8541 0.04478 0.04075 -0.0742 1.0000 0.0283 -13.000 -0.8742 0.03925 0.03513 -0.0785 1.0000 0.0283 -12.750 -0.8793 0.03420 0.02997 -0.0833 1.0000 0.0285 -12.500 -0.8722 0.03002 0.02566 -0.0875 1.0000 0.0287 -12.250 -0.8577 0.02698 0.02248 -0.0903 1.0000 0.0290 -12.000 -0.8233 0.02495 0.02032 -0.0945 0.9963 0.0293 -11.750 -0.7894 0.02339 0.01866 -0.0977 0.9907 0.0297 -11.500 -0.7572 0.02210 0.01727 -0.1000 0.9840 0.0300 -11.250 -0.7260 0.02100 0.01607 -0.1017 0.9758 0.0304 -11.000 -0.6915 0.01999 0.01497 -0.1038 0.9671 0.0309 -10.750 -0.6564 0.01910 0.01397 -0.1058 0.9550 0.0314 -10.500 -0.6189 0.01828 0.01304 -0.1081 0.9408 0.0318 -10.250 -0.5794 0.01727 0.01195 -0.1110 0.9220 0.0323 -10.000 -0.5427 0.01649 0.01105 -0.1131 0.8943 0.0328 -9.500 -0.4880 0.01549 0.00973 -0.1128 0.8368 0.0338 -9.250 -0.4630 0.01509 0.00918 -0.1121 0.8160 0.0344 -9.000 -0.4377 0.01473 0.00868 -0.1114 0.7990 0.0349 -8.750 -0.4121 0.01438 0.00820 -0.1108 0.7846 0.0355 -8.500 -0.3864 0.01398 0.00772 -0.1102 0.7723 0.0363 -8.000 -0.3343 0.01327 0.00684 -0.1090 0.7492 0.0385 -7.750 -0.3080 0.01299 0.00646 -0.1084 0.7392 0.0397 -7.500 -0.2812 0.01265 0.00609 -0.1079 0.7292 0.0416 -7.000 -0.2275 0.01216 0.00557 -0.1069 0.7086 0.0503 -6.750 -0.2000 0.01209 0.00548 -0.1063 0.6986 0.0577 -6.500 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0.3762 0.01098 0.00296 -0.0956 0.4333 0.0930 -1.250 0.4036 0.01097 0.00290 -0.0951 0.4259 0.0942 -1.000 0.4314 0.01095 0.00286 -0.0947 0.4189 0.0956 -0.750 0.4590 0.01094 0.00283 -0.0943 0.4108 0.0972 -0.500 0.4864 0.01097 0.00281 -0.0938 0.4037 0.0989 -0.250 0.5142 0.01096 0.00279 -0.0934 0.3972 0.1013 0.000 0.5416 0.01096 0.00279 -0.0929 0.3899 0.1056 0.250 0.5689 0.01097 0.00279 -0.0925 0.3830 0.1130 0.750 0.6227 0.01085 0.00284 -0.0916 0.3671 0.1843 1.000 0.6500 0.01082 0.00290 -0.0912 0.3601 0.2189 1.250 0.6768 0.01084 0.00298 -0.0907 0.3523 0.2489 1.500 0.7037 0.01088 0.00306 -0.0902 0.3448 0.2753 1.750 0.7305 0.01096 0.00315 -0.0897 0.3359 0.2955 2.000 0.7572 0.01105 0.00326 -0.0892 0.3276 0.3135 2.250 0.7838 0.01114 0.00337 -0.0886 0.3194 0.3323 2.500 0.8102 0.01127 0.00349 -0.0881 0.3115 0.3470 2.750 0.8366 0.01139 0.00361 -0.0875 0.3024 0.3612 3.250 0.8889 0.01168 0.00390 -0.0864 0.2857 0.3898 3.500 0.9145 0.01185 0.00407 -0.0857 0.2778 0.4063 3.750 0.9404 0.01200 0.00423 -0.0851 0.2699 0.4211 4.000 0.9656 0.01221 0.00441 -0.0845 0.2622 0.4340 4.250 0.9914 0.01236 0.00458 -0.0838 0.2554 0.4464 4.500 1.0164 0.01257 0.00478 -0.0831 0.2484 0.4605 4.750 1.0415 0.01275 0.00498 -0.0825 0.2425 0.4764 5.000 1.0666 0.01292 0.00518 -0.0818 0.2367 0.4952 5.500 1.1155 0.01331 0.00563 -0.0802 0.2267 0.5296 6.000 1.1635 0.01365 0.00609 -0.0786 0.2173 0.5821 6.250 1.1831 0.01359 0.00636 -0.0770 0.2133 0.7131 6.750 1.2558 0.01380 0.00693 -0.0805 0.2047 1.0000 7.000 1.2788 0.01411 0.00720 -0.0796 0.2005 1.0000 7.250 1.3012 0.01444 0.00751 -0.0786 0.1968 1.0000 7.500 1.3249 0.01468 0.00777 -0.0777 0.1939 1.0000 7.750 1.3478 0.01496 0.00804 -0.0768 0.1902 1.0000 8.000 1.3696 0.01529 0.00836 -0.0757 0.1863 1.0000 8.250 1.3903 0.01567 0.00871 -0.0745 0.1825 1.0000 8.500 1.4122 0.01596 0.00902 -0.0734 0.1794 1.0000 8.750 1.4333 0.01628 0.00935 -0.0723 0.1753 1.0000 9.000 1.4527 0.01667 0.00972 -0.0709 0.1708 1.0000 9.250 1.4707 0.01708 0.01012 -0.0693 0.1668 1.0000 9.500 1.4889 0.01742 0.01048 -0.0677 0.1633 1.0000 9.750 1.5052 0.01781 0.01088 -0.0658 0.1594 1.0000 10.000 1.5196 0.01829 0.01136 -0.0637 0.1558 1.0000 10.250 1.5348 0.01876 0.01184 -0.0618 0.1527 1.0000 10.500 1.5505 0.01922 0.01233 -0.0600 0.1495 1.0000 10.750 1.5649 0.01975 0.01288 -0.0582 0.1461 1.0000 11.000 1.5771 0.02042 0.01355 -0.0562 0.1425 1.0000 11.250 1.5904 0.02106 0.01422 -0.0544 0.1394 1.0000 11.500 1.6036 0.02174 0.01493 -0.0527 0.1363 1.0000 11.750 1.6149 0.02256 0.01578 -0.0510 0.1329 1.0000 12.000 1.6244 0.02354 0.01677 -0.0493 0.1300 1.0000 12.250 1.6355 0.02448 0.01776 -0.0479 0.1276 1.0000 12.500 1.6462 0.02550 0.01883 -0.0466 0.1249 1.0000 12.750 1.6553 0.02670 0.02007 -0.0454 0.1222 1.0000 13.000 1.6624 0.02812 0.02152 -0.0442 0.1196 1.0000 13.250 1.6690 0.02966 0.02311 -0.0432 0.1172 1.0000 13.500 1.6775 0.03110 0.02461 -0.0423 0.1151 1.0000 13.750 1.6841 0.03276 0.02633 -0.0415 0.1127 1.0000 14.000 1.6886 0.03467 0.02829 -0.0409 0.1103 1.0000 14.250 1.6901 0.03691 0.03058 -0.0403 0.1080 1.0000 14.500 1.6926 0.03914 0.03287 -0.0398 0.1061 1.0000 14.750 1.6960 0.04132 0.03514 -0.0395 0.1042 1.0000 15.000 1.6972 0.04377 0.03766 -0.0392 0.1024 1.0000 15.250 1.6961 0.04655 0.04051 -0.0391 0.1005 1.0000 15.500 1.6925 0.04970 0.04373 -0.0392 0.0987 1.0000 15.750 1.6863 0.05326 0.04735 -0.0395 0.0971 1.0000 16.000 1.6843 0.05640 0.05059 -0.0398 0.0957 1.0000 16.250 1.6817 0.05968 0.05395 -0.0403 0.0940 1.0000 16.500 1.6773 0.06323 0.05759 -0.0408 0.0926 1.0000 16.750 1.6698 0.06723 0.06167 -0.0416 0.0907 1.0000 17.000 1.6597 0.07167 0.06617 -0.0426 0.0889 1.0000 17.250 1.6482 0.07635 0.07092 -0.0438 0.0873 1.0000 17.500 1.6436 0.08013 0.07480 -0.0446 0.0858 1.0000 17.750 1.6359 0.08443 0.07919 -0.0458 0.0841 1.0000 18.000 1.6263 0.08905 0.08388 -0.0472 0.0824 1.0000 18.250 1.6150 0.09399 0.08890 -0.0488 0.0808 1.0000