XFOIL Version 6.96 Calculated polar for: GOE 625 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6533 0.08495 0.08165 -0.0939 0.9922 0.0411 -16.500 -0.8508 0.05126 0.04738 -0.1195 0.9743 0.0411 -16.250 -0.8974 0.03821 0.03394 -0.1329 0.9564 0.0413 -16.000 -0.9063 0.03341 0.02891 -0.1375 0.9407 0.0418 -15.750 -0.9084 0.03062 0.02593 -0.1388 0.9275 0.0423 -15.500 -0.9069 0.02866 0.02382 -0.1387 0.9163 0.0428 -15.250 -0.9014 0.02721 0.02227 -0.1381 0.9061 0.0434 -15.000 -0.8931 0.02609 0.02105 -0.1369 0.8975 0.0441 -14.750 -0.8829 0.02518 0.02006 -0.1355 0.8893 0.0450 -14.500 -0.8724 0.02444 0.01921 -0.1337 0.8822 0.0458 -14.250 -0.8567 0.02370 0.01835 -0.1327 0.8762 0.0468 -14.000 -0.8395 0.02303 0.01760 -0.1317 0.8694 0.0477 -13.750 -0.8203 0.02249 0.01699 -0.1308 0.8625 0.0485 -13.500 -0.7998 0.02198 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-4.000 0.1722 0.01317 0.00478 -0.1164 0.4937 0.0853 -3.750 0.1982 0.01315 0.00469 -0.1160 0.4837 0.0863 -3.500 0.2244 0.01309 0.00459 -0.1157 0.4759 0.0876 -3.250 0.2508 0.01304 0.00452 -0.1154 0.4687 0.0889 -2.750 0.3036 0.01300 0.00441 -0.1148 0.4572 0.0921 -2.500 0.3305 0.01298 0.00437 -0.1146 0.4524 0.0939 -2.250 0.3569 0.01297 0.00434 -0.1143 0.4478 0.0966 -2.000 0.3829 0.01297 0.00433 -0.1140 0.4436 0.1007 -1.750 0.4093 0.01296 0.00434 -0.1137 0.4402 0.1066 -1.500 0.4363 0.01293 0.00435 -0.1136 0.4370 0.1158 -1.250 0.4629 0.01294 0.00438 -0.1134 0.4337 0.1264 -1.000 0.4892 0.01297 0.00442 -0.1131 0.4303 0.1361 -0.750 0.5152 0.01302 0.00447 -0.1127 0.4271 0.1434 -0.500 0.5409 0.01309 0.00452 -0.1124 0.4243 0.1501 -0.250 0.5668 0.01316 0.00458 -0.1120 0.4218 0.1554 0.000 0.5935 0.01318 0.00463 -0.1118 0.4200 0.1614 0.250 0.6200 0.01322 0.00469 -0.1116 0.4181 0.1667 0.500 0.6462 0.01326 0.00475 -0.1113 0.4161 0.1724 0.750 0.6721 0.01331 0.00482 -0.1110 0.4140 0.1789 1.000 0.6976 0.01339 0.00490 -0.1106 0.4117 0.1848 1.250 0.7226 0.01346 0.00498 -0.1102 0.4093 0.1911 1.500 0.7469 0.01356 0.00508 -0.1096 0.4067 0.1982 2.000 0.7944 0.01373 0.00530 -0.1082 0.4017 0.2190 2.250 0.8184 0.01374 0.00540 -0.1076 0.3996 0.2401 2.500 0.8418 0.01372 0.00552 -0.1070 0.3972 0.2823 2.750 0.8648 0.01363 0.00567 -0.1063 0.3945 0.3694 3.000 0.8880 0.01358 0.00585 -0.1058 0.3915 0.4548 3.250 0.9112 0.01348 0.00608 -0.1052 0.3885 0.5758 3.500 0.9321 0.01325 0.00639 -0.1041 0.3858 0.7582 3.750 0.9481 0.01313 0.00671 -0.1013 0.3838 0.9347 4.000 0.9830 0.01326 0.00685 -0.1030 0.3822 1.0000 4.250 1.0066 0.01343 0.00702 -0.1024 0.3804 1.0000 4.500 1.0299 0.01363 0.00721 -0.1018 0.3782 1.0000 4.750 1.0529 0.01384 0.00740 -0.1012 0.3758 1.0000 5.000 1.0755 0.01408 0.00762 -0.1005 0.3733 1.0000 5.250 1.0977 0.01434 0.00785 -0.0998 0.3710 1.0000 5.500 1.1197 0.01462 0.00811 -0.0991 0.3689 1.0000 5.750 1.1411 0.01495 0.00840 -0.0983 0.3667 1.0000 6.000 1.1648 0.01518 0.00865 -0.0979 0.3649 1.0000 6.250 1.1883 0.01542 0.00891 -0.0975 0.3629 1.0000 6.500 1.2112 0.01570 0.00919 -0.0970 0.3606 1.0000 6.750 1.2333 0.01600 0.00950 -0.0965 0.3579 1.0000 7.000 1.2546 0.01634 0.00984 -0.0958 0.3550 1.0000 7.250 1.2749 0.01673 0.01021 -0.0950 0.3520 1.0000 7.500 1.2947 0.01716 0.01062 -0.0942 0.3489 1.0000 7.750 1.3172 0.01748 0.01097 -0.0938 0.3456 1.0000 8.000 1.3380 0.01787 0.01138 -0.0932 0.3411 1.0000 8.250 1.3566 0.01837 0.01186 -0.0923 0.3364 1.0000 8.500 1.3748 0.01891 0.01238 -0.0914 0.3323 1.0000 8.750 1.3957 0.01933 0.01283 -0.0909 0.3283 1.0000 9.000 1.4149 0.01984 0.01336 -0.0902 0.3236 1.0000 9.250 1.4319 0.02048 0.01398 -0.0893 0.3188 1.0000 9.500 1.4497 0.02109 0.01460 -0.0884 0.3141 1.0000 9.750 1.4672 0.02172 0.01525 -0.0876 0.3079 1.0000 10.000 1.4805 0.02261 0.01610 -0.0864 0.3014 1.0000 10.250 1.4965 0.02336 0.01686 -0.0855 0.2942 1.0000 10.750 1.5208 0.02539 0.01886 -0.0831 0.2788 1.0000 11.000 1.5296 0.02666 0.02010 -0.0816 0.2713 1.0000 11.250 1.5417 0.02773 0.02118 -0.0806 0.2647 1.0000 11.500 1.5506 0.02907 0.02252 -0.0793 0.2583 1.0000 11.750 1.5607 0.03036 0.02381 -0.0782 0.2533 1.0000 12.000 1.5713 0.03164 0.02511 -0.0771 0.2485 1.0000 12.250 1.5799 0.03309 0.02657 -0.0760 0.2439 1.0000 12.500 1.5866 0.03473 0.02823 -0.0748 0.2398 1.0000 12.750 1.5965 0.03615 0.02968 -0.0740 0.2355 1.0000 13.000 1.6027 0.03791 0.03146 -0.0729 0.2306 1.0000 13.250 1.6052 0.04002 0.03357 -0.0717 0.2261 1.0000 13.500 1.6131 0.04170 0.03529 -0.0710 0.2224 1.0000 13.750 1.6192 0.04359 0.03723 -0.0701 0.2185 1.0000 14.000 1.6226 0.04576 0.03943 -0.0693 0.2147 1.0000 14.250 1.6239 0.04816 0.04186 -0.0684 0.2114 1.0000 14.500 1.6285 0.05030 0.04405 -0.0677 0.2087 1.0000 14.750 1.6348 0.05228 0.04610 -0.0672 0.2060 1.0000 15.000 1.6384 0.05458 0.04845 -0.0667 0.2033 1.0000 15.250 1.6395 0.05717 0.05110 -0.0661 0.2005 1.0000 15.500 1.6378 0.06010 0.05407 -0.0655 0.1976 1.0000 15.750 1.6367 0.06297 0.05699 -0.0651 0.1950 1.0000 16.000 1.6401 0.06541 0.05951 -0.0648 0.1925 1.0000 16.250 1.6416 0.06808 0.06225 -0.0645 0.1896 1.0000 16.500 1.6399 0.07114 0.06537 -0.0643 0.1867 1.0000 16.750 1.6351 0.07460 0.06888 -0.0641 0.1839 1.0000 17.000 1.6292 0.07818 0.07251 -0.0639 0.1812 1.0000 17.250 1.6311 0.08087 0.07528 -0.0639 0.1784 1.0000 17.500 1.6280 0.08420 0.07868 -0.0639 0.1747 1.0000 17.750 1.6197 0.08820 0.08272 -0.0640 0.1704 1.0000 18.000 1.6138 0.09190 0.08646 -0.0642 0.1668 1.0000 18.250 1.6100 0.09535 0.08998 -0.0644 0.1623 1.0000 18.500 1.6016 0.09940 0.09407 -0.0648 0.1571 1.0000 18.750 1.5947 0.10331 0.09802 -0.0652 0.1525 1.0000 19.000 1.5855 0.10754 0.10229 -0.0657 0.1458 1.0000 19.250 1.5744 0.11203 0.10679 -0.0664 0.1377 1.0000