XFOIL Version 6.96 Calculated polar for: GOE 645 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.6784 0.14191 0.13974 -0.0292 1.0000 0.0190 -18.750 -0.7092 0.13169 0.12941 -0.0349 1.0000 0.0193 -18.500 -0.7246 0.12472 0.12238 -0.0387 1.0000 0.0196 -18.250 -0.7491 0.11632 0.11387 -0.0435 1.0000 0.0199 -18.000 -0.7633 0.10993 0.10741 -0.0471 1.0000 0.0201 -17.750 -0.7788 0.10350 0.10089 -0.0507 1.0000 0.0204 -17.500 -0.7915 0.09771 0.09503 -0.0539 1.0000 0.0205 -17.250 -0.8046 0.09198 0.08922 -0.0571 1.0000 0.0207 -17.000 -0.8177 0.08632 0.08347 -0.0604 1.0000 0.0209 -16.750 -0.8296 0.08096 0.07803 -0.0635 1.0000 0.0212 -16.500 -0.8395 0.07612 0.07312 -0.0662 1.0000 0.0213 -16.250 -0.8516 0.07102 0.06794 -0.0692 1.0000 0.0215 -16.000 -0.8638 0.06631 0.06315 -0.0718 1.0000 0.0215 -15.750 -0.8782 0.06154 0.05831 -0.0745 1.0000 0.0216 -15.500 -0.8953 0.05669 0.05339 -0.0771 1.0000 0.0217 -15.250 -0.9183 0.05142 0.04806 -0.0799 1.0000 0.0219 -15.000 -0.9439 0.04591 0.04246 -0.0827 1.0000 0.0220 -14.750 -0.9722 0.04006 0.03653 -0.0857 1.0000 0.0220 -14.500 -1.0086 0.03105 0.02732 -0.0942 1.0000 0.0219 -14.250 -1.0349 0.02848 0.02462 -0.0910 1.0000 0.0219 -14.000 -1.0441 0.02663 0.02270 -0.0880 1.0000 0.0222 -13.750 -1.0449 0.02535 0.02137 -0.0851 1.0000 0.0224 -13.500 -1.0185 0.02428 0.02025 -0.0865 0.9986 0.0229 -13.250 -0.9865 0.02330 0.01921 -0.0887 0.9965 0.0233 -13.000 -0.9524 0.02247 0.01833 -0.0910 0.9943 0.0239 -12.750 -0.9195 0.02163 0.01741 -0.0929 0.9916 0.0244 -12.500 -0.8864 0.02095 0.01667 -0.0945 0.9879 0.0250 -12.250 -0.8519 0.02030 0.01593 -0.0964 0.9848 0.0253 -12.000 -0.8216 0.01881 0.01438 -0.0985 0.9818 0.0261 -11.750 -0.7953 0.01810 0.01365 -0.0988 0.9748 0.0266 -11.500 -0.7622 0.01748 0.01299 -0.1002 0.9704 0.0272 -11.250 -0.7322 0.01695 0.01242 -0.1009 0.9622 0.0279 -10.750 -0.6554 0.01591 0.01125 -0.1055 0.9460 0.0291 -10.500 -0.6174 0.01498 0.01023 -0.1082 0.9311 0.0299 -10.250 -0.5834 0.01433 0.00948 -0.1098 0.9086 0.0307 -10.000 -0.5561 0.01399 0.00902 -0.1097 0.8828 0.0314 -9.750 -0.5320 0.01372 0.00863 -0.1089 0.8590 0.0321 -9.500 -0.5085 0.01347 0.00827 -0.1080 0.8383 0.0328 -9.250 -0.4849 0.01325 0.00792 -0.1070 0.8200 0.0334 -9.000 -0.4606 0.01303 0.00760 -0.1062 0.8043 0.0338 -8.750 -0.4393 0.01247 0.00694 -0.1050 0.7909 0.0348 -8.500 -0.4155 0.01215 0.00655 -0.1042 0.7786 0.0358 -8.250 -0.3905 0.01191 0.00625 -0.1035 0.7669 0.0367 -8.000 -0.3653 0.01167 0.00594 -0.1028 0.7562 0.0375 -7.750 -0.3399 0.01147 0.00565 -0.1021 0.7461 0.0383 -7.500 -0.3137 0.01127 0.00539 -0.1016 0.7373 0.0389 -7.250 -0.2895 0.01088 0.00494 -0.1008 0.7279 0.0406 -7.000 -0.2634 0.01064 0.00466 -0.1002 0.7191 0.0419 -6.750 -0.2374 0.01046 0.00441 -0.0997 0.7097 0.0432 -6.500 -0.2105 0.01029 0.00419 -0.0992 0.7012 0.0444 -6.250 -0.1851 0.01001 0.00386 -0.0986 0.6923 0.0469 -6.000 -0.1584 0.00979 0.00362 -0.0981 0.6838 0.0495 -5.750 -0.1324 0.00958 0.00336 -0.0975 0.6742 0.0534 -5.500 -0.1063 0.00929 0.00308 -0.0970 0.6645 0.0618 -5.250 -0.0812 0.00898 0.00289 -0.0964 0.6540 0.0950 -5.000 -0.0539 0.00887 0.00279 -0.0960 0.6436 0.1053 -4.750 -0.0271 0.00877 0.00267 -0.0956 0.6330 0.1121 -4.500 -0.0001 0.00872 0.00257 -0.0951 0.6209 0.1174 -4.250 0.0271 0.00866 0.00246 -0.0947 0.6081 0.1217 -4.000 0.0537 0.00859 0.00236 -0.0943 0.5944 0.1268 -3.750 0.0803 0.00857 0.00226 -0.0938 0.5790 0.1309 -3.500 0.1069 0.00855 0.00218 -0.0933 0.5644 0.1358 -3.000 0.1599 0.00842 0.00203 -0.0923 0.5374 0.1572 -2.750 0.1860 0.00836 0.00198 -0.0918 0.5231 0.1782 -2.500 0.2124 0.00832 0.00196 -0.0913 0.5108 0.1994 -2.250 0.2391 0.00832 0.00195 -0.0909 0.4992 0.2153 -2.000 0.2665 0.00833 0.00195 -0.0905 0.4904 0.2271 -1.750 0.2935 0.00835 0.00196 -0.0901 0.4817 0.2398 -1.500 0.3210 0.00836 0.00197 -0.0899 0.4744 0.2484 -1.250 0.3481 0.00840 0.00198 -0.0895 0.4657 0.2553 -1.000 0.3756 0.00845 0.00198 -0.0892 0.4575 0.2604 -0.750 0.4027 0.00847 0.00199 -0.0888 0.4498 0.2671 -0.500 0.4299 0.00851 0.00201 -0.0885 0.4432 0.2728 -0.250 0.4576 0.00855 0.00203 -0.0882 0.4370 0.2771 0.000 0.4844 0.00859 0.00205 -0.0878 0.4303 0.2838 0.250 0.5117 0.00862 0.00208 -0.0875 0.4245 0.2898 0.500 0.5391 0.00867 0.00211 -0.0872 0.4184 0.2948 0.750 0.5656 0.00872 0.00215 -0.0868 0.4119 0.3026 1.000 0.5929 0.00875 0.00219 -0.0865 0.4068 0.3090 1.250 0.6200 0.00881 0.00222 -0.0862 0.4004 0.3142 1.500 0.6462 0.00888 0.00228 -0.0857 0.3938 0.3220 1.750 0.6735 0.00890 0.00233 -0.0854 0.3886 0.3293 2.000 0.7000 0.00896 0.00238 -0.0850 0.3820 0.3378 2.250 0.7262 0.00903 0.00245 -0.0846 0.3755 0.3479 2.500 0.7528 0.00907 0.00251 -0.0842 0.3686 0.3599 3.000 0.8045 0.00919 0.00267 -0.0832 0.3535 0.3930 3.250 0.8294 0.00927 0.00277 -0.0826 0.3448 0.4190 3.500 0.8544 0.00925 0.00288 -0.0819 0.3374 0.4681 3.750 0.8766 0.00919 0.00304 -0.0809 0.3273 0.5725 4.000 0.9532 0.00867 0.00340 -0.0916 0.3110 1.0000 4.250 0.9765 0.00884 0.00352 -0.0906 0.3011 1.0000 4.500 0.9992 0.00905 0.00366 -0.0895 0.2915 1.0000 4.750 1.0214 0.00927 0.00381 -0.0883 0.2811 1.0000 5.000 1.0441 0.00947 0.00396 -0.0873 0.2721 1.0000 5.250 1.0659 0.00972 0.00414 -0.0861 0.2629 1.0000 5.500 1.0885 0.00992 0.00431 -0.0850 0.2557 1.0000 5.750 1.1101 0.01017 0.00450 -0.0838 0.2480 1.0000 6.000 1.1328 0.01036 0.00467 -0.0828 0.2423 1.0000 6.250 1.1543 0.01061 0.00487 -0.0816 0.2360 1.0000 6.500 1.1766 0.01081 0.00506 -0.0805 0.2314 1.0000 6.750 1.1989 0.01101 0.00525 -0.0794 0.2268 1.0000 7.000 1.2199 0.01126 0.00547 -0.0782 0.2217 1.0000 7.250 1.2411 0.01150 0.00569 -0.0770 0.2168 1.0000 7.500 1.2626 0.01171 0.00589 -0.0758 0.2121 1.0000 7.750 1.2821 0.01200 0.00615 -0.0743 0.2062 1.0000 8.000 1.3015 0.01224 0.00638 -0.0728 0.2015 1.0000 8.250 1.3198 0.01248 0.00661 -0.0710 0.1963 1.0000 8.500 1.3353 0.01282 0.00692 -0.0688 0.1891 1.0000 8.750 1.3523 0.01312 0.00720 -0.0670 0.1802 1.0000 9.000 1.3650 0.01363 0.00761 -0.0645 0.1641 1.0000 9.250 1.3667 0.01461 0.00838 -0.0604 0.1343 1.0000 9.500 1.3797 0.01516 0.00890 -0.0582 0.1285 1.0000 9.750 1.3928 0.01573 0.00946 -0.0561 0.1232 1.0000 10.000 1.4080 0.01623 0.00997 -0.0544 0.1213 1.0000 10.250 1.4230 0.01676 0.01051 -0.0527 0.1199 1.0000 10.500 1.4371 0.01735 0.01112 -0.0511 0.1182 1.0000 10.750 1.4504 0.01803 0.01182 -0.0494 0.1162 1.0000 11.000 1.4646 0.01870 0.01252 -0.0480 0.1150 1.0000 11.250 1.4784 0.01942 0.01327 -0.0466 0.1139 1.0000 11.500 1.4910 0.02026 0.01415 -0.0452 0.1124 1.0000 11.750 1.5052 0.02104 0.01498 -0.0441 0.1119 1.0000 12.000 1.5201 0.02181 0.01580 -0.0432 0.1114 1.0000 12.250 1.5340 0.02269 0.01673 -0.0422 0.1108 1.0000 12.500 1.5472 0.02364 0.01774 -0.0413 0.1105 1.0000 12.750 1.5599 0.02466 0.01882 -0.0405 0.1093 1.0000 13.000 1.5714 0.02581 0.02002 -0.0397 0.1084 1.0000 13.250 1.5813 0.02712 0.02138 -0.0388 0.1072 1.0000 13.500 1.5905 0.02852 0.02283 -0.0380 0.1063 1.0000 13.750 1.5978 0.03013 0.02448 -0.0373 0.1051 1.0000 14.000 1.6029 0.03196 0.02637 -0.0365 0.1038 1.0000 14.250 1.6064 0.03396 0.02843 -0.0358 0.1024 1.0000 14.500 1.6063 0.03637 0.03091 -0.0351 0.1007 1.0000 14.750 1.6129 0.03819 0.03279 -0.0347 0.1000 1.0000 15.000 1.6240 0.03958 0.03424 -0.0344 0.0994 1.0000 15.250 1.6336 0.04115 0.03588 -0.0341 0.0984 1.0000 15.500 1.6407 0.04299 0.03778 -0.0338 0.0972 1.0000 15.750 1.6477 0.04488 0.03972 -0.0336 0.0949 1.0000 16.000 1.6494 0.04734 0.04223 -0.0334 0.0932 1.0000 16.250 1.6455 0.05047 0.04541 -0.0333 0.0907 1.0000 16.500 1.6466 0.05311 0.04810 -0.0333 0.0886 1.0000 16.750 1.6566 0.05476 0.04982 -0.0333 0.0858 1.0000 17.000 1.6535 0.05793 0.05297 -0.0334 0.0786 1.0000 17.250 1.6341 0.06303 0.05799 -0.0338 0.0621 1.0000 17.500 1.5993 0.07017 0.06512 -0.0347 0.0513 1.0000 17.750 1.5716 0.07662 0.07162 -0.0357 0.0453 1.0000 18.000 1.5487 0.08260 0.07767 -0.0367 0.0410 1.0000