XFOIL Version 6.96 Calculated polar for: GOE 574 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.2428 0.08735 0.08516 -0.0578 0.9813 0.0068 -8.250 -0.2315 0.08419 0.08201 -0.0607 0.9780 0.0058 -8.000 -0.2347 0.07967 0.07752 -0.0626 0.9714 0.0068 -7.500 -0.2624 0.07536 0.07330 -0.0576 0.9226 0.0067 -7.250 -0.2327 0.06814 0.06600 -0.0688 0.9022 0.0067 -7.000 -0.1900 0.05870 0.05641 -0.0850 0.8859 0.0067 -6.750 -0.1372 0.04569 0.04305 -0.1054 0.8645 0.0072 -6.500 -0.0865 0.03677 0.03364 -0.1187 0.8356 0.0076 -6.250 -0.0710 0.03028 0.02666 -0.1202 0.8097 0.0082 -6.000 -0.0849 0.02036 0.01578 -0.1143 0.7926 0.0092 -5.750 -0.0835 0.01503 0.00943 -0.1095 0.7773 0.0105 -5.500 -0.0603 0.01473 0.00895 -0.1086 0.7601 0.0114 -5.250 -0.0366 0.01473 0.00883 -0.1078 0.7435 0.0122 -5.000 -0.0142 0.01440 0.00830 -0.1066 0.7276 0.0137 -4.750 0.0071 0.01366 0.00726 -0.1052 0.7124 0.0155 -4.500 0.0298 0.01364 0.00716 -0.1042 0.6966 0.0165 -4.250 0.0528 0.01369 0.00713 -0.1033 0.6807 0.0177 -4.000 0.0753 0.01348 0.00675 -0.1021 0.6652 0.0195 -3.750 0.0983 0.01335 0.00645 -0.1011 0.6496 0.0217 -3.500 0.1215 0.01325 0.00618 -0.1001 0.6345 0.0231 -3.250 0.1450 0.01330 0.00608 -0.0991 0.6192 0.0238 -3.000 0.1658 0.01233 0.00495 -0.0978 0.6046 0.0259 -2.750 0.1883 0.01204 0.00455 -0.0968 0.5896 0.0271 -2.500 0.2112 0.01183 0.00423 -0.0957 0.5747 0.0286 -2.250 0.2340 0.01162 0.00390 -0.0947 0.5603 0.0299 -2.000 0.2570 0.01139 0.00357 -0.0937 0.5473 0.0306 -1.750 0.2800 0.01122 0.00329 -0.0927 0.5353 0.0313 -1.500 0.3030 0.01107 0.00305 -0.0916 0.5239 0.0317 -1.000 0.3494 0.01083 0.00265 -0.0898 0.5035 0.0325 -0.750 0.3729 0.01076 0.00251 -0.0889 0.4952 0.0330 -0.500 0.3963 0.01067 0.00236 -0.0880 0.4871 0.0331 -0.250 0.4199 0.01061 0.00223 -0.0871 0.4802 0.0330 0.000 0.4438 0.01056 0.00212 -0.0863 0.4738 0.0330 0.250 0.4674 0.01054 0.00204 -0.0855 0.4677 0.0331 0.500 0.4917 0.01053 0.00198 -0.0848 0.4623 0.0331 0.750 0.5156 0.01053 0.00193 -0.0840 0.4574 0.0335 1.000 0.5396 0.01055 0.00191 -0.0832 0.4533 0.0337 1.250 0.5640 0.01055 0.00189 -0.0825 0.4497 0.0351 1.500 0.5878 0.01055 0.00190 -0.0817 0.4459 0.0431 1.750 0.6090 0.01035 0.00199 -0.0805 0.4427 0.1644 2.250 0.8248 0.00953 0.00311 -0.1182 0.4332 1.0000 2.500 0.8472 0.00962 0.00319 -0.1172 0.4304 1.0000 2.750 0.8692 0.00974 0.00328 -0.1160 0.4275 1.0000 3.000 0.8912 0.00985 0.00338 -0.1149 0.4243 1.0000 3.250 0.9137 0.00993 0.00348 -0.1139 0.4206 1.0000 3.500 0.9355 0.01003 0.00359 -0.1127 0.4163 1.0000 3.750 0.9560 0.01018 0.00370 -0.1113 0.4098 1.0000 4.000 0.9772 0.01026 0.00382 -0.1100 0.4013 1.0000 4.250 0.9974 0.01041 0.00394 -0.1085 0.3947 1.0000 4.500 1.0184 0.01050 0.00406 -0.1072 0.3863 1.0000 4.750 1.0373 0.01066 0.00418 -0.1054 0.3705 1.0000 5.000 1.0552 0.01086 0.00432 -0.1035 0.3484 1.0000 5.250 1.0605 0.01171 0.00468 -0.0992 0.2569 1.0000 5.500 1.0563 0.01320 0.00559 -0.0933 0.1552 1.0000 5.750 1.0430 0.01480 0.00662 -0.0854 0.0256 1.0000 6.000 1.0553 0.01515 0.00697 -0.0823 0.0167 1.0000 6.250 1.0693 0.01545 0.00733 -0.0796 0.0147 1.0000 6.500 1.0819 0.01581 0.00777 -0.0767 0.0125 1.0000 6.750 1.0930 0.01627 0.00831 -0.0735 0.0107 1.0000 7.000 1.1026 0.01682 0.00897 -0.0700 0.0096 1.0000 7.250 1.1161 0.01720 0.00940 -0.0674 0.0087 1.0000 7.500 1.1280 0.01768 0.00994 -0.0646 0.0080 1.0000 7.750 1.1376 0.01828 0.01061 -0.0614 0.0076 1.0000 8.000 1.1474 0.01889 0.01128 -0.0583 0.0071 1.0000 8.250 1.1543 0.01965 0.01213 -0.0549 0.0067 1.0000 8.500 1.1575 0.02062 0.01320 -0.0510 0.0064 1.0000 8.750 1.1590 0.02172 0.01440 -0.0470 0.0061 1.0000 9.000 1.1622 0.02281 0.01558 -0.0435 0.0060 1.0000 9.250 1.1647 0.02400 0.01687 -0.0401 0.0057 1.0000 9.500 1.1746 0.02483 0.01776 -0.0381 0.0052 1.0000 9.750 1.1704 0.02664 0.01970 -0.0345 0.0052 1.0000 10.000 1.1850 0.02730 0.02038 -0.0334 0.0046 1.0000 10.250 1.1779 0.02963 0.02284 -0.0303 0.0047 1.0000 10.500 1.1865 0.03089 0.02414 -0.0291 0.0044 1.0000 10.750 1.1857 0.03303 0.02637 -0.0272 0.0043 1.0000 11.000 1.1775 0.03595 0.02938 -0.0252 0.0040 1.0000 11.250 1.1766 0.03835 0.03189 -0.0238 0.0040 1.0000 11.500 1.1780 0.04058 0.03424 -0.0226 0.0039 1.0000 11.750 1.1784 0.04295 0.03671 -0.0213 0.0038 1.0000 12.000 1.1791 0.04530 0.03917 -0.0198 0.0037 1.0000 12.250 1.1813 0.04749 0.04145 -0.0185 0.0037 1.0000 12.500 1.1854 0.04954 0.04362 -0.0169 0.0036 1.0000 12.750 1.1912 0.05149 0.04569 -0.0153 0.0035 1.0000 13.000 1.1985 0.05341 0.04775 -0.0134 0.0034 1.0000 13.250 1.2051 0.05549 0.04996 -0.0121 0.0034 1.0000 13.500 1.2112 0.05789 0.05254 -0.0105 0.0033 1.0000 13.750 1.2139 0.06056 0.05537 -0.0095 0.0031 1.0000 14.000 1.2145 0.06330 0.05826 -0.0090 0.0030 1.0000 14.250 1.2127 0.06690 0.06208 -0.0079 0.0031 1.0000 14.500 1.2098 0.06962 0.06486 -0.0088 0.0028 1.0000 14.750 1.2059 0.07309 0.06846 -0.0090 0.0028 1.0000 15.000 1.2025 0.07617 0.07161 -0.0102 0.0026 1.0000 15.250 1.1941 0.08070 0.07635 -0.0102 0.0027 1.0000 15.500 1.1886 0.08452 0.08031 -0.0114 0.0026 1.0000 15.750 1.1690 0.09138 0.08751 -0.0114 0.0027 1.0000 16.000 1.1698 0.09399 0.09009 -0.0138 0.0026 1.0000 16.250 1.1556 0.09984 0.09615 -0.0152 0.0026 1.0000 16.500 1.1464 0.10480 0.10121 -0.0174 0.0025 1.0000 16.750 1.1283 0.11181 0.10846 -0.0195 0.0026 1.0000 17.000 1.1136 0.11825 0.11504 -0.0223 0.0026 1.0000 17.250 1.1030 0.12394 0.12082 -0.0255 0.0025 1.0000 17.500 1.0861 0.13147 0.12854 -0.0287 0.0025 1.0000 17.750 1.0751 0.13782 0.13499 -0.0323 0.0025 1.0000 18.000 1.0463 0.14935 0.14676 -0.0379 0.0026 1.0000 18.250 1.0412 0.15490 0.15237 -0.0415 0.0025 1.0000 18.500 1.0267 0.16347 0.16102 -0.0466 0.0025 1.0000 18.750 0.9700 0.19160 0.18938 -0.0600 0.0029 1.0000