XFOIL Version 6.96 Calculated polar for: GOE 685 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.7257 0.10110 0.09790 -0.0517 1.0000 0.0249 -16.000 -0.7482 0.09344 0.09011 -0.0561 1.0000 0.0251 -15.750 -0.7652 0.08697 0.08353 -0.0599 1.0000 0.0253 -15.500 -0.7796 0.08113 0.07759 -0.0633 1.0000 0.0255 -15.250 -0.7914 0.07582 0.07218 -0.0664 1.0000 0.0257 -15.000 -0.8020 0.07095 0.06722 -0.0692 1.0000 0.0258 -14.750 -0.8131 0.06626 0.06244 -0.0720 1.0000 0.0260 -14.500 -0.8247 0.06188 0.05799 -0.0745 1.0000 0.0261 -14.250 -0.8332 0.05826 0.05433 -0.0762 1.0000 0.0263 -14.000 -0.8442 0.05441 0.05045 -0.0781 1.0000 0.0265 -13.750 -0.8588 0.05033 0.04635 -0.0800 1.0000 0.0266 -13.500 -0.8788 0.04605 0.04202 -0.0816 1.0000 0.0267 -13.250 -0.9217 0.04116 0.03709 -0.0817 1.0000 0.0265 -13.000 -0.9278 0.03440 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0.1724 -3.000 0.1208 0.00934 0.00235 -0.1039 0.6629 0.1786 -2.750 0.1478 0.00930 0.00229 -0.1035 0.6509 0.1864 -2.500 0.1749 0.00929 0.00224 -0.1032 0.6376 0.1948 -2.250 0.2016 0.00927 0.00219 -0.1028 0.6234 0.2020 -2.000 0.2285 0.00928 0.00215 -0.1024 0.6098 0.2079 -1.750 0.2553 0.00930 0.00211 -0.1020 0.5969 0.2131 -1.500 0.2823 0.00930 0.00209 -0.1016 0.5832 0.2200 -1.250 0.3089 0.00935 0.00207 -0.1012 0.5675 0.2264 -1.000 0.3352 0.00940 0.00206 -0.1007 0.5498 0.2322 -0.750 0.3613 0.00948 0.00207 -0.1002 0.5314 0.2385 -0.500 0.3876 0.00957 0.00208 -0.0997 0.5147 0.2438 -0.250 0.4140 0.00963 0.00211 -0.0993 0.5002 0.2498 0.000 0.4404 0.00972 0.00214 -0.0988 0.4862 0.2556 0.250 0.4666 0.00982 0.00218 -0.0983 0.4720 0.2609 0.500 0.4927 0.00992 0.00224 -0.0979 0.4593 0.2670 0.750 0.5193 0.01001 0.00229 -0.0974 0.4489 0.2729 1.000 0.5458 0.01010 0.00235 -0.0970 0.4400 0.2775 1.250 0.5723 0.01017 0.00241 -0.0966 0.4320 0.2826 1.500 0.5988 0.01025 0.00249 -0.0962 0.4253 0.2878 1.750 0.6256 0.01033 0.00255 -0.0959 0.4189 0.2924 2.000 0.6519 0.01042 0.00264 -0.0954 0.4125 0.2977 2.250 0.6784 0.01049 0.00273 -0.0951 0.4068 0.3036 2.500 0.7050 0.01058 0.00282 -0.0947 0.4007 0.3092 2.750 0.7308 0.01069 0.00292 -0.0942 0.3942 0.3140 3.000 0.7572 0.01076 0.00302 -0.0938 0.3875 0.3196 3.250 0.7830 0.01089 0.00313 -0.0933 0.3792 0.3258 3.500 0.8090 0.01098 0.00325 -0.0928 0.3738 0.3334 3.750 0.8352 0.01106 0.00337 -0.0924 0.3678 0.3428 4.000 0.8605 0.01118 0.00351 -0.0918 0.3608 0.3515 4.250 0.8863 0.01127 0.00364 -0.0913 0.3538 0.3610 4.500 0.9117 0.01138 0.00378 -0.0908 0.3468 0.3713 4.750 0.9368 0.01150 0.00393 -0.0902 0.3409 0.3828 5.250 0.9856 0.01175 0.00427 -0.0888 0.3183 0.4198 5.500 1.0077 0.01193 0.00448 -0.0878 0.2978 0.4638 6.000 1.0566 0.01212 0.00534 -0.0873 0.2165 1.0000 6.250 1.0732 0.01280 0.00580 -0.0854 0.1835 1.0000 6.500 1.0935 0.01321 0.00614 -0.0841 0.1725 1.0000 6.750 1.1145 0.01356 0.00647 -0.0829 0.1655 1.0000 7.000 1.1350 0.01392 0.00680 -0.0816 0.1593 1.0000 7.250 1.1565 0.01421 0.00709 -0.0805 0.1546 1.0000 7.500 1.1765 0.01456 0.00744 -0.0791 0.1489 1.0000 7.750 1.1950 0.01493 0.00780 -0.0774 0.1435 1.0000 8.000 1.2144 0.01521 0.00810 -0.0759 0.1376 1.0000 8.250 1.2307 0.01563 0.00848 -0.0739 0.1271 1.0000 8.500 1.2356 0.01662 0.00919 -0.0703 0.0823 1.0000 8.750 1.2472 0.01730 0.00984 -0.0678 0.0732 1.0000 9.000 1.2600 0.01793 0.01047 -0.0655 0.0674 1.0000 9.250 1.2749 0.01846 0.01103 -0.0636 0.0631 1.0000 9.500 1.2882 0.01910 0.01168 -0.0615 0.0584 1.0000 9.750 1.3020 0.01972 0.01233 -0.0596 0.0541 1.0000 10.000 1.3142 0.02045 0.01305 -0.0576 0.0496 1.0000 10.250 1.3269 0.02117 0.01379 -0.0557 0.0460 1.0000 10.500 1.3381 0.02200 0.01462 -0.0537 0.0429 1.0000 10.750 1.3498 0.02283 0.01548 -0.0519 0.0409 1.0000 11.000 1.3609 0.02373 0.01641 -0.0502 0.0389 1.0000 11.250 1.3706 0.02475 0.01746 -0.0484 0.0373 1.0000 11.500 1.3794 0.02587 0.01862 -0.0466 0.0359 1.0000 11.750 1.3895 0.02696 0.01976 -0.0451 0.0348 1.0000 12.000 1.3983 0.02817 0.02103 -0.0436 0.0338 1.0000 12.250 1.4061 0.02951 0.02244 -0.0421 0.0329 1.0000 12.500 1.4126 0.03103 0.02400 -0.0408 0.0320 1.0000 12.750 1.4172 0.03277 0.02579 -0.0395 0.0311 1.0000 13.000 1.4224 0.03454 0.02762 -0.0384 0.0304 1.0000 13.250 1.4285 0.03629 0.02946 -0.0375 0.0298 1.0000 13.500 1.4336 0.03820 0.03145 -0.0366 0.0291 1.0000 13.750 1.4377 0.04026 0.03359 -0.0359 0.0284 1.0000 14.000 1.4406 0.04253 0.03593 -0.0353 0.0278 1.0000 14.250 1.4419 0.04503 0.03850 -0.0349 0.0272 1.0000 14.500 1.4417 0.04779 0.04132 -0.0345 0.0267 1.0000 14.750 1.4389 0.05094 0.04455 -0.0344 0.0261 1.0000 15.000 1.4394 0.05381 0.04750 -0.0344 0.0258 1.0000 15.250 1.4404 0.05667 0.05046 -0.0345 0.0253 1.0000 15.500 1.4403 0.05976 0.05365 -0.0347 0.0248 1.0000 15.750 1.4393 0.06303 0.05702 -0.0351 0.0243 1.0000 16.000 1.4379 0.06642 0.06049 -0.0356 0.0239 1.0000 16.250 1.4363 0.06990 0.06406 -0.0362 0.0234 1.0000 16.500 1.4331 0.07369 0.06793 -0.0370 0.0230 1.0000 16.750 1.4297 0.07757 0.07188 -0.0378 0.0226 1.0000 17.000 1.4248 0.08172 0.07611 -0.0389 0.0222 1.0000 17.250 1.4184 0.08614 0.08060 -0.0401 0.0218 1.0000