XFOIL Version 6.96 Calculated polar for: GOE 478 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.6440 0.03653 0.03394 -0.1126 0.9833 0.0279 -11.500 -0.6489 0.03199 0.02908 -0.1147 0.9709 0.0280 -11.250 -0.6369 0.02918 0.02601 -0.1160 0.9596 0.0283 -11.000 -0.6138 0.02625 0.02279 -0.1190 0.9512 0.0285 -10.750 -0.5826 0.02393 0.02019 -0.1224 0.9423 0.0287 -10.500 -0.5528 0.02208 0.01807 -0.1248 0.9284 0.0289 -10.250 -0.5265 0.02077 0.01652 -0.1258 0.9109 0.0291 -10.000 -0.5059 0.01981 0.01534 -0.1251 0.8918 0.0293 -9.750 -0.4873 0.01909 0.01441 -0.1238 0.8728 0.0294 -9.250 -0.4490 0.01798 0.01296 -0.1209 0.8398 0.0297 -9.000 -0.4320 0.01686 0.01165 -0.1193 0.8269 0.0300 -8.750 -0.4137 0.01586 0.01052 -0.1179 0.8158 0.0303 -8.500 -0.3924 0.01525 0.00982 -0.1167 0.8059 0.0305 -8.250 -0.3698 0.01482 0.00932 -0.1158 0.7978 0.0308 -8.000 -0.3463 0.01441 0.00886 -0.1150 0.7912 0.0311 -7.750 -0.3225 0.01406 0.00843 -0.1142 0.7850 0.0314 -7.500 -0.2981 0.01375 0.00807 -0.1135 0.7797 0.0318 -7.250 -0.2735 0.01337 0.00763 -0.1128 0.7750 0.0322 -7.000 -0.2490 0.01300 0.00720 -0.1121 0.7701 0.0325 -6.750 -0.2245 0.01267 0.00679 -0.1114 0.7651 0.0328 -6.500 -0.1993 0.01233 0.00640 -0.1108 0.7613 0.0331 -6.250 -0.1738 0.01200 0.00604 -0.1102 0.7581 0.0334 -6.000 -0.1480 0.01173 0.00572 -0.1097 0.7548 0.0337 -5.750 -0.1224 0.01143 0.00537 -0.1091 0.7514 0.0340 -5.500 -0.0990 0.01090 0.00479 -0.1083 0.7475 0.0346 -5.250 -0.0733 0.01063 0.00451 -0.1077 0.7437 0.0352 -5.000 -0.0471 0.01040 0.00428 -0.1073 0.7409 0.0358 -4.750 -0.0208 0.01018 0.00406 -0.1068 0.7377 0.0364 -4.500 0.0055 0.00999 0.00384 -0.1063 0.7343 0.0370 -4.250 0.0318 0.00983 0.00364 -0.1058 0.7303 0.0377 -4.000 0.0589 0.00974 0.00351 -0.1055 0.7260 0.0383 -3.750 0.0842 0.00941 0.00318 -0.1049 0.7234 0.0394 -3.500 0.1108 0.00922 0.00301 -0.1044 0.7203 0.0404 -3.250 0.1375 0.00907 0.00286 -0.1040 0.7170 0.0415 -3.000 0.1643 0.00895 0.00272 -0.1036 0.7133 0.0427 -2.750 0.1907 0.00881 0.00254 -0.1031 0.7090 0.0442 -2.500 0.2173 0.00865 0.00240 -0.1027 0.7053 0.0462 -2.250 0.2441 0.00852 0.00229 -0.1022 0.7014 0.0483 -2.000 0.2705 0.00836 0.00214 -0.1017 0.6971 0.0518 -1.750 0.2967 0.00823 0.00202 -0.1012 0.6924 0.0572 -1.500 0.3227 0.00808 0.00192 -0.1007 0.6876 0.0700 -1.250 0.3488 0.00790 0.00188 -0.1002 0.6825 0.0994 -1.000 0.3752 0.00782 0.00182 -0.0997 0.6759 0.1110 -0.750 0.4011 0.00775 0.00177 -0.0991 0.6690 0.1210 -0.500 0.4276 0.00765 0.00172 -0.0986 0.6609 0.1322 -0.250 0.4529 0.00758 0.00168 -0.0979 0.6514 0.1515 0.000 0.4781 0.00750 0.00167 -0.0972 0.6376 0.1813 0.250 0.5022 0.00750 0.00165 -0.0962 0.6163 0.1988 0.500 0.5235 0.00760 0.00165 -0.0947 0.5795 0.2133 0.750 0.5442 0.00777 0.00170 -0.0931 0.5493 0.2286 1.000 0.5668 0.00787 0.00177 -0.0919 0.5311 0.2478 1.500 0.6085 0.00746 0.00192 -0.0892 0.5086 0.4854 1.750 0.6227 0.00703 0.00205 -0.0863 0.4991 0.6986 2.000 0.6371 0.00664 0.00219 -0.0831 0.4907 0.8818 2.250 0.7039 0.00686 0.00245 -0.0914 0.4777 0.9677 2.500 0.7517 0.00702 0.00257 -0.0956 0.4694 0.9822 3.000 0.8401 0.00736 0.00280 -0.1026 0.4534 0.9959 3.250 0.8883 0.00754 0.00290 -0.1070 0.4448 0.9999 3.500 0.9107 0.00762 0.00296 -0.1058 0.4399 1.0000 3.750 0.9319 0.00769 0.00303 -0.1043 0.4343 1.0000 4.000 0.9516 0.00782 0.00311 -0.1026 0.4277 1.0000 4.250 0.9722 0.00792 0.00320 -0.1010 0.4216 1.0000 4.500 0.9930 0.00802 0.00328 -0.0995 0.4144 1.0000 4.750 1.0119 0.00818 0.00339 -0.0975 0.4069 1.0000 5.000 1.0335 0.00827 0.00348 -0.0962 0.4000 1.0000 5.250 1.0524 0.00844 0.00359 -0.0943 0.3907 1.0000 5.500 1.0734 0.00855 0.00370 -0.0928 0.3830 1.0000 5.750 1.0923 0.00873 0.00383 -0.0909 0.3737 1.0000 6.000 1.1125 0.00888 0.00395 -0.0893 0.3634 1.0000 6.250 1.1308 0.00909 0.00410 -0.0873 0.3509 1.0000 6.500 1.1485 0.00932 0.00428 -0.0853 0.3375 1.0000 6.750 1.1647 0.00958 0.00447 -0.0829 0.3221 1.0000 7.000 1.1781 0.00987 0.00467 -0.0800 0.3044 1.0000 7.250 1.1902 0.01021 0.00492 -0.0769 0.2837 1.0000 7.500 1.2012 0.01063 0.00523 -0.0737 0.2615 1.0000 7.750 1.2128 0.01109 0.00557 -0.0707 0.2409 1.0000 8.000 1.2259 0.01153 0.00592 -0.0680 0.2232 1.0000 8.250 1.2395 0.01198 0.00629 -0.0656 0.2073 1.0000 8.500 1.2536 0.01244 0.00668 -0.0632 0.1935 1.0000 8.750 1.2683 0.01289 0.00707 -0.0610 0.1812 1.0000 9.000 1.2839 0.01332 0.00745 -0.0590 0.1705 1.0000 9.250 1.2993 0.01378 0.00787 -0.0571 0.1608 1.0000 9.750 1.3296 0.01477 0.00879 -0.0533 0.1428 1.0000 10.000 1.3442 0.01532 0.00931 -0.0515 0.1346 1.0000 10.250 1.3584 0.01591 0.00986 -0.0496 0.1265 1.0000 10.500 1.3731 0.01650 0.01043 -0.0479 0.1189 1.0000 10.750 1.3860 0.01721 0.01110 -0.0461 0.1109 1.0000 11.000 1.3995 0.01791 0.01178 -0.0444 0.1034 1.0000 11.250 1.4123 0.01867 0.01252 -0.0427 0.0962 1.0000 11.500 1.4236 0.01956 0.01337 -0.0409 0.0887 1.0000 11.750 1.4350 0.02046 0.01425 -0.0392 0.0823 1.0000 12.000 1.4465 0.02139 0.01517 -0.0376 0.0770 1.0000 12.250 1.4564 0.02245 0.01621 -0.0360 0.0727 1.0000 12.500 1.4684 0.02340 0.01720 -0.0346 0.0699 1.0000 12.750 1.4796 0.02443 0.01824 -0.0333 0.0676 1.0000 13.000 1.4887 0.02563 0.01945 -0.0318 0.0653 1.0000 13.250 1.4972 0.02692 0.02077 -0.0304 0.0634 1.0000 13.500 1.5093 0.02797 0.02187 -0.0294 0.0622 1.0000 13.750 1.5190 0.02921 0.02316 -0.0282 0.0610 1.0000 14.000 1.5277 0.03055 0.02453 -0.0271 0.0595 1.0000 14.250 1.5340 0.03213 0.02612 -0.0259 0.0577 1.0000 14.500 1.5383 0.03392 0.02795 -0.0246 0.0563 1.0000 14.750 1.5486 0.03521 0.02931 -0.0238 0.0555 1.0000 15.000 1.5569 0.03671 0.03086 -0.0229 0.0547 1.0000 15.250 1.5641 0.03834 0.03255 -0.0221 0.0538 1.0000 15.500 1.5699 0.04012 0.03438 -0.0213 0.0530 1.0000 15.750 1.5741 0.04210 0.03641 -0.0205 0.0521 1.0000 16.000 1.5756 0.04439 0.03874 -0.0197 0.0511 1.0000 16.250 1.5743 0.04702 0.04144 -0.0190 0.0503 1.0000 16.500 1.5777 0.04925 0.04373 -0.0185 0.0496 1.0000 16.750 1.5844 0.05118 0.04573 -0.0182 0.0490 1.0000 17.000 1.5871 0.05357 0.04820 -0.0179 0.0486 1.0000 17.250 1.5906 0.05592 0.05062 -0.0177 0.0478 1.0000 17.500 1.5926 0.05850 0.05327 -0.0176 0.0473 1.0000 17.750 1.5937 0.06123 0.05606 -0.0176 0.0466 1.0000 18.000 1.5929 0.06421 0.05909 -0.0177 0.0458 1.0000 18.250 1.5898 0.06751 0.06245 -0.0179 0.0452 1.0000 18.500 1.5816 0.07146 0.06648 -0.0183 0.0443 1.0000 18.750 1.5775 0.07496 0.07006 -0.0187 0.0439 1.0000 19.000 1.5794 0.07772 0.07289 -0.0190 0.0434 1.0000 19.250 1.5803 0.08056 0.07581 -0.0194 0.0429 1.0000