XFOIL Version 6.96 Calculated polar for: GOE 476 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.3254 0.16207 0.16016 -0.0377 1.0000 0.0289 -15.500 -0.3186 0.15982 0.15793 -0.0382 1.0000 0.0296 -15.000 -0.9880 0.03469 0.03173 -0.1131 0.9991 0.0373 -14.750 -0.9708 0.03260 0.02954 -0.1160 0.9964 0.0376 -14.500 -0.9539 0.03059 0.02740 -0.1182 0.9930 0.0379 -14.250 -0.9413 0.02893 0.02561 -0.1185 0.9879 0.0382 -14.000 -0.9181 0.02746 0.02403 -0.1199 0.9844 0.0385 -13.750 -0.8937 0.02593 0.02236 -0.1215 0.9819 0.0389 -13.500 -0.8709 0.02481 0.02113 -0.1220 0.9783 0.0392 -13.250 -0.8480 0.02394 0.02015 -0.1222 0.9733 0.0396 -13.000 -0.8203 0.02310 0.01920 -0.1231 0.9701 0.0399 -12.750 -0.7944 0.02154 0.01748 -0.1245 0.9674 0.0403 -12.500 -0.7749 0.02037 0.01623 -0.1240 0.9594 0.0408 -12.250 -0.7411 0.01960 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0.2290 0.00916 0.00255 -0.1010 0.6068 0.0714 -2.250 0.2548 0.00912 0.00249 -0.1004 0.6022 0.0738 -2.000 0.2817 0.00903 0.00241 -0.1000 0.5994 0.0761 -1.750 0.3080 0.00890 0.00231 -0.0995 0.5960 0.0796 -1.500 0.3342 0.00882 0.00225 -0.0990 0.5922 0.0836 -1.250 0.3599 0.00875 0.00218 -0.0983 0.5882 0.0890 -1.000 0.3853 0.00872 0.00215 -0.0977 0.5837 0.0972 -0.750 0.4117 0.00862 0.00214 -0.0972 0.5806 0.1104 -0.500 0.4381 0.00855 0.00213 -0.0967 0.5761 0.1233 -0.250 0.4638 0.00854 0.00212 -0.0961 0.5704 0.1322 0.000 0.4890 0.00857 0.00215 -0.0954 0.5649 0.1401 0.250 0.5160 0.00854 0.00214 -0.0950 0.5609 0.1453 0.500 0.5420 0.00851 0.00214 -0.0945 0.5562 0.1527 0.750 0.5676 0.00853 0.00215 -0.0939 0.5512 0.1576 1.000 0.5927 0.00855 0.00215 -0.0931 0.5455 0.1621 1.250 0.6187 0.00851 0.00215 -0.0926 0.5400 0.1686 1.500 0.6439 0.00852 0.00216 -0.0919 0.5342 0.1739 1.750 0.6682 0.00856 0.00218 -0.0910 0.5285 0.1797 2.000 0.6940 0.00852 0.00220 -0.0905 0.5235 0.1884 2.750 0.7659 0.00847 0.00232 -0.0877 0.5051 0.2601 3.000 0.7821 0.00808 0.00243 -0.0854 0.4977 0.4622 3.250 0.8791 0.00741 0.00301 -0.1006 0.4879 0.9801 3.500 0.9351 0.00767 0.00319 -0.1066 0.4797 0.9881 3.750 0.9782 0.00786 0.00335 -0.1099 0.4724 0.9931 4.000 1.0285 0.00801 0.00343 -0.1148 0.4631 0.9969 4.250 1.0717 0.00816 0.00352 -0.1182 0.4526 0.9995 4.750 1.1173 0.00843 0.00371 -0.1161 0.4361 1.0000 5.000 1.1368 0.00858 0.00383 -0.1144 0.4292 1.0000 5.250 1.1557 0.00873 0.00395 -0.1125 0.4228 1.0000 5.500 1.1757 0.00885 0.00406 -0.1109 0.4157 1.0000 6.000 1.2120 0.00917 0.00433 -0.1069 0.4005 1.0000 6.250 1.2289 0.00935 0.00448 -0.1047 0.3929 1.0000 6.500 1.2463 0.00951 0.00463 -0.1025 0.3858 1.0000 6.750 1.2625 0.00968 0.00478 -0.1002 0.3769 1.0000 7.000 1.2760 0.00987 0.00494 -0.0973 0.3675 1.0000 7.250 1.2840 0.01010 0.00512 -0.0932 0.3555 1.0000 7.500 1.2927 0.01037 0.00533 -0.0894 0.3390 1.0000 7.750 1.2979 0.01079 0.00562 -0.0851 0.3121 1.0000 8.000 1.2945 0.01153 0.00614 -0.0793 0.2744 1.0000 8.250 1.2957 0.01224 0.00670 -0.0746 0.2475 1.0000 8.500 1.3038 0.01281 0.00719 -0.0712 0.2328 1.0000 8.750 1.3143 0.01332 0.00766 -0.0684 0.2226 1.0000 9.000 1.3265 0.01382 0.00813 -0.0659 0.2148 1.0000 9.250 1.3394 0.01432 0.00861 -0.0636 0.2080 1.0000 9.500 1.3541 0.01476 0.00906 -0.0617 0.2028 1.0000 9.750 1.3668 0.01533 0.00962 -0.0595 0.1971 1.0000 10.000 1.3807 0.01587 0.01016 -0.0576 0.1922 1.0000 10.250 1.3960 0.01638 0.01068 -0.0560 0.1873 1.0000 10.500 1.4081 0.01706 0.01135 -0.0540 0.1814 1.0000 10.750 1.4215 0.01772 0.01201 -0.0523 0.1762 1.0000 11.000 1.4356 0.01837 0.01267 -0.0508 0.1708 1.0000 11.250 1.4459 0.01925 0.01353 -0.0489 0.1642 1.0000 11.500 1.4594 0.02000 0.01430 -0.0474 0.1592 1.0000 11.750 1.4700 0.02094 0.01523 -0.0458 0.1526 1.0000 12.000 1.4803 0.02194 0.01623 -0.0442 0.1459 1.0000 12.250 1.4883 0.02313 0.01739 -0.0425 0.1383 1.0000 12.500 1.4963 0.02437 0.01862 -0.0409 0.1307 1.0000 12.750 1.5015 0.02585 0.02008 -0.0392 0.1230 1.0000 13.000 1.5059 0.02743 0.02163 -0.0376 0.1143 1.0000 13.250 1.5083 0.02923 0.02341 -0.0359 0.1046 1.0000 13.500 1.5093 0.03121 0.02536 -0.0343 0.0948 1.0000 13.750 1.5059 0.03360 0.02769 -0.0326 0.0828 1.0000 14.000 1.5030 0.03606 0.03010 -0.0312 0.0733 1.0000 14.250 1.5043 0.03821 0.03226 -0.0300 0.0684 1.0000 14.500 1.5053 0.04044 0.03449 -0.0289 0.0647 1.0000 14.750 1.5091 0.04248 0.03657 -0.0281 0.0629 1.0000 15.000 1.5116 0.04466 0.03878 -0.0273 0.0611 1.0000 15.250 1.5133 0.04695 0.04110 -0.0265 0.0593 1.0000 15.500 1.5145 0.04935 0.04354 -0.0258 0.0580 1.0000 15.750 1.5204 0.05128 0.04553 -0.0253 0.0570 1.0000 16.000 1.5239 0.05350 0.04781 -0.0248 0.0562 1.0000 16.250 1.5273 0.05576 0.05012 -0.0243 0.0554 1.0000 16.500 1.5282 0.05828 0.05269 -0.0239 0.0543 1.0000 16.750 1.5278 0.06100 0.05545 -0.0235 0.0533 1.0000 17.000 1.5265 0.06385 0.05834 -0.0232 0.0522 1.0000 17.250 1.5258 0.06671 0.06127 -0.0230 0.0515 1.0000 17.500 1.5306 0.06894 0.06356 -0.0229 0.0511 1.0000 17.750 1.5327 0.07151 0.06620 -0.0228 0.0506 1.0000 18.000 1.5357 0.07396 0.06872 -0.0228 0.0500 1.0000 18.250 1.5361 0.07680 0.07162 -0.0228 0.0494 1.0000 18.500 1.5380 0.07945 0.07433 -0.0229 0.0488 1.0000 18.750 1.5369 0.08252 0.07745 -0.0231 0.0481 1.0000 19.000 1.5353 0.08562 0.08061 -0.0233 0.0476 1.0000 19.250 1.5318 0.08904 0.08408 -0.0237 0.0469 1.0000