XFOIL Version 6.96 Calculated polar for: GOE 646 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.8848 0.08574 0.08221 -0.0811 1.0000 0.0304 -18.000 -0.8959 0.08143 0.07785 -0.0828 1.0000 0.0306 -17.750 -0.9079 0.07711 0.07347 -0.0845 1.0000 0.0309 -17.500 -0.9152 0.07233 0.06862 -0.0878 0.9996 0.0310 -17.250 -0.9186 0.06776 0.06398 -0.0915 0.9990 0.0314 -17.000 -0.9233 0.06304 0.05918 -0.0954 0.9982 0.0316 -16.750 -0.9297 0.05820 0.05424 -0.0996 0.9970 0.0317 -16.500 -0.9344 0.05358 0.04953 -0.1037 0.9955 0.0320 -16.250 -0.9388 0.04894 0.04480 -0.1081 0.9936 0.0321 -16.000 -0.9445 0.04445 0.04022 -0.1119 0.9911 0.0323 -15.750 -0.9519 0.03985 0.03552 -0.1156 0.9876 0.0325 -15.500 -0.9554 0.03512 0.03070 -0.1204 0.9838 0.0329 -15.000 -0.9515 0.02773 0.02312 -0.1276 0.9714 0.0335 -14.750 -0.9443 0.02490 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0.0570 -10.000 -0.4903 0.01198 0.00621 -0.1418 0.8131 0.0600 -9.750 -0.4667 0.01178 0.00596 -0.1411 0.8070 0.0625 -9.500 -0.4432 0.01153 0.00570 -0.1403 0.8014 0.0652 -9.250 -0.4189 0.01132 0.00548 -0.1396 0.7947 0.0677 -9.000 -0.3948 0.01115 0.00526 -0.1389 0.7878 0.0698 -8.750 -0.3704 0.01094 0.00503 -0.1382 0.7818 0.0724 -8.500 -0.3456 0.01076 0.00483 -0.1376 0.7746 0.0747 -8.250 -0.3211 0.01063 0.00465 -0.1369 0.7670 0.0766 -8.000 -0.2964 0.01042 0.00443 -0.1362 0.7594 0.0794 -7.750 -0.2720 0.01027 0.00425 -0.1354 0.7501 0.0821 -7.500 -0.2470 0.01015 0.00408 -0.1348 0.7406 0.0842 -7.250 -0.2237 0.01001 0.00389 -0.1338 0.7283 0.0873 -7.000 -0.1995 0.00988 0.00372 -0.1330 0.7143 0.0903 -6.750 -0.1757 0.00979 0.00358 -0.1320 0.6991 0.0933 -6.500 -0.1526 0.00968 0.00342 -0.1310 0.6838 0.0977 -6.000 -0.1058 0.00948 0.00314 -0.1290 0.6549 0.1104 -5.750 -0.0820 0.00934 0.00300 -0.1282 0.6432 0.1213 -5.500 -0.0586 0.00922 0.00288 -0.1272 0.6321 0.1335 -5.250 -0.0337 0.00909 0.00277 -0.1265 0.6229 0.1444 -4.750 0.0165 0.00893 0.00259 -0.1252 0.6070 0.1614 -4.500 0.0417 0.00886 0.00252 -0.1245 0.5993 0.1689 -4.250 0.0668 0.00882 0.00245 -0.1238 0.5923 0.1762 -4.000 0.0928 0.00873 0.00238 -0.1233 0.5861 0.1851 -3.750 0.1183 0.00870 0.00233 -0.1227 0.5791 0.1925 -3.500 0.1432 0.00866 0.00229 -0.1219 0.5724 0.2011 -3.250 0.1694 0.00862 0.00225 -0.1214 0.5656 0.2082 -3.000 0.1946 0.00859 0.00221 -0.1207 0.5587 0.2164 -2.750 0.2198 0.00858 0.00219 -0.1200 0.5530 0.2242 -2.500 0.2463 0.00853 0.00216 -0.1196 0.5492 0.2319 -2.250 0.2723 0.00851 0.00215 -0.1190 0.5437 0.2404 -2.000 0.2973 0.00852 0.00214 -0.1183 0.5375 0.2470 -1.750 0.3225 0.00851 0.00214 -0.1176 0.5322 0.2560 -1.500 0.3489 0.00849 0.00213 -0.1171 0.5283 0.2632 -1.250 0.3745 0.00849 0.00213 -0.1165 0.5231 0.2700 -1.000 0.3993 0.00851 0.00214 -0.1157 0.5176 0.2765 -0.750 0.4241 0.00853 0.00215 -0.1149 0.5128 0.2843 -0.500 0.4500 0.00852 0.00217 -0.1144 0.5087 0.2904 -0.250 0.4751 0.00853 0.00218 -0.1136 0.5047 0.2950 0.000 0.4993 0.00856 0.00219 -0.1127 0.5008 0.2987 0.250 0.5225 0.00857 0.00221 -0.1116 0.4968 0.3048 0.500 0.5466 0.00859 0.00224 -0.1106 0.4933 0.3103 0.750 0.5716 0.00861 0.00226 -0.1099 0.4894 0.3150 1.000 0.5958 0.00864 0.00229 -0.1090 0.4843 0.3191 1.250 0.6190 0.00867 0.00233 -0.1079 0.4795 0.3257 1.500 0.6423 0.00873 0.00238 -0.1068 0.4749 0.3315 1.750 0.6671 0.00877 0.00243 -0.1061 0.4695 0.3370 2.000 0.6900 0.00882 0.00249 -0.1050 0.4626 0.3438 2.250 0.7120 0.00892 0.00257 -0.1036 0.4556 0.3504 2.500 0.7353 0.00900 0.00265 -0.1026 0.4471 0.3561 2.750 0.7562 0.00913 0.00275 -0.1011 0.4371 0.3625 3.000 0.7780 0.00924 0.00286 -0.0998 0.4253 0.3693 3.250 0.7978 0.00943 0.00299 -0.0982 0.4089 0.3753 3.500 0.8162 0.00966 0.00314 -0.0963 0.3903 0.3816 3.750 0.8339 0.00989 0.00332 -0.0943 0.3730 0.3898 4.000 0.8521 0.01014 0.00351 -0.0924 0.3576 0.3969 4.250 0.8706 0.01038 0.00371 -0.0906 0.3443 0.4044 4.750 0.9084 0.01080 0.00410 -0.0872 0.3241 0.4230 5.000 0.9268 0.01102 0.00432 -0.0854 0.3158 0.4371 5.250 0.9467 0.01118 0.00451 -0.0839 0.3093 0.4533 5.500 0.9661 0.01134 0.00472 -0.0824 0.3033 0.4743 5.750 0.9829 0.01158 0.00499 -0.0804 0.2957 0.5004 6.000 1.0017 0.01173 0.00522 -0.0788 0.2888 0.5347 6.250 1.0180 0.01200 0.00553 -0.0768 0.2802 0.5688 6.500 1.0357 0.01221 0.00580 -0.0750 0.2737 0.5988 6.750 1.0539 0.01244 0.00608 -0.0733 0.2679 0.6215 7.000 1.0709 0.01273 0.00638 -0.0715 0.2620 0.6388 7.250 1.0888 0.01300 0.00667 -0.0699 0.2564 0.6541 7.500 1.1061 0.01328 0.00698 -0.0682 0.2502 0.6688 7.750 1.1209 0.01365 0.00736 -0.0661 0.2426 0.6849 8.000 1.1388 0.01391 0.00768 -0.0645 0.2389 0.7021 8.250 1.1531 0.01430 0.00809 -0.0625 0.2302 0.7221 8.500 1.1673 0.01462 0.00851 -0.0603 0.2249 0.7557 9.000 1.2845 0.01558 0.00980 -0.0750 0.2018 1.0000 9.250 1.3005 0.01619 0.01038 -0.0736 0.1937 1.0000 9.500 1.3175 0.01678 0.01093 -0.0723 0.1865 1.0000 9.750 1.3327 0.01746 0.01158 -0.0709 0.1798 1.0000 10.000 1.3489 0.01811 0.01221 -0.0697 0.1733 1.0000 10.250 1.3626 0.01890 0.01298 -0.0682 0.1668 1.0000 10.500 1.3793 0.01955 0.01362 -0.0671 0.1625 1.0000 10.750 1.3927 0.02039 0.01444 -0.0657 0.1565 1.0000 11.000 1.4070 0.02119 0.01524 -0.0644 0.1520 1.0000 11.250 1.4219 0.02198 0.01604 -0.0633 0.1476 1.0000 11.500 1.4344 0.02294 0.01698 -0.0619 0.1428 1.0000 11.750 1.4479 0.02385 0.01790 -0.0607 0.1388 1.0000 12.000 1.4609 0.02480 0.01886 -0.0596 0.1340 1.0000 12.250 1.4702 0.02603 0.02006 -0.0581 0.1274 1.0000 12.500 1.4796 0.02729 0.02130 -0.0568 0.1190 1.0000 12.750 1.4815 0.02911 0.02305 -0.0549 0.1053 1.0000 13.000 1.4785 0.03138 0.02522 -0.0529 0.0887 1.0000 13.250 1.4798 0.03341 0.02722 -0.0514 0.0806 1.0000 13.500 1.4857 0.03514 0.02896 -0.0502 0.0765 1.0000 13.750 1.4922 0.03687 0.03071 -0.0492 0.0738 1.0000 14.000 1.4972 0.03876 0.03263 -0.0482 0.0711 1.0000 14.250 1.5052 0.04043 0.03433 -0.0475 0.0691 1.0000 14.500 1.5120 0.04227 0.03620 -0.0467 0.0676 1.0000 14.750 1.5179 0.04420 0.03817 -0.0460 0.0662 1.0000 15.000 1.5228 0.04624 0.04024 -0.0454 0.0648 1.0000 15.250 1.5278 0.04832 0.04237 -0.0448 0.0636 1.0000 15.500 1.5348 0.05022 0.04432 -0.0443 0.0628 1.0000 15.750 1.5404 0.05229 0.04645 -0.0439 0.0620 1.0000 16.000 1.5452 0.05446 0.04867 -0.0435 0.0611 1.0000 16.250 1.5491 0.05673 0.05098 -0.0431 0.0602 1.0000 16.500 1.5513 0.05920 0.05351 -0.0427 0.0594 1.0000 16.750 1.5532 0.06172 0.05606 -0.0424 0.0583 1.0000 17.000 1.5536 0.06446 0.05886 -0.0422 0.0574 1.0000 17.250 1.5572 0.06684 0.06129 -0.0420 0.0566 1.0000 17.500 1.5590 0.06945 0.06397 -0.0419 0.0560 1.0000 17.750 1.5611 0.07202 0.06659 -0.0418 0.0552 1.0000 18.000 1.5613 0.07487 0.06950 -0.0418 0.0543 1.0000 18.250 1.5612 0.07775 0.07244 -0.0418 0.0536 1.0000 18.500 1.5595 0.08087 0.07560 -0.0420 0.0527 1.0000 18.750 1.5559 0.08421 0.07900 -0.0421 0.0517 1.0000 19.000 1.5538 0.08740 0.08225 -0.0424 0.0512 1.0000