XFOIL Version 6.96 Calculated polar for: GOE 482 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.4207 0.03229 0.02883 -0.1687 0.7330 0.0341 -12.750 -0.4252 0.02351 0.01974 -0.1839 0.7283 0.0344 -12.500 -0.4026 0.02178 0.01785 -0.1868 0.7237 0.0348 -12.250 -0.3785 0.02068 0.01661 -0.1883 0.7190 0.0352 -12.000 -0.3534 0.01983 0.01561 -0.1894 0.7149 0.0354 -11.750 -0.3275 0.01897 0.01466 -0.1905 0.7109 0.0358 -11.500 -0.3009 0.01837 0.01401 -0.1912 0.7061 0.0362 -11.250 -0.2730 0.01817 0.01379 -0.1915 0.7009 0.0366 -11.000 -0.2453 0.01792 0.01349 -0.1918 0.6957 0.0369 -10.750 -0.2172 0.01770 0.01324 -0.1921 0.6894 0.0373 -10.500 -0.1897 0.01741 0.01287 -0.1923 0.6827 0.0376 -10.250 -0.1613 0.01729 0.01271 -0.1925 0.6768 0.0381 -10.000 -0.1335 0.01696 0.01230 -0.1929 0.6699 0.0386 -9.750 -0.1063 0.01643 0.01165 -0.1933 0.6631 0.0389 -9.500 -0.0787 0.01586 0.01097 -0.1938 0.6555 0.0392 -9.250 -0.0514 0.01536 0.01034 -0.1942 0.6468 0.0394 -9.000 -0.0236 0.01489 0.00975 -0.1946 0.6375 0.0396 -8.750 0.0041 0.01451 0.00924 -0.1948 0.6278 0.0399 -8.500 0.0322 0.01419 0.00882 -0.1951 0.6179 0.0401 -8.250 0.0601 0.01387 0.00838 -0.1953 0.6086 0.0403 -8.000 0.0880 0.01357 0.00797 -0.1954 0.5978 0.0404 -7.750 0.1160 0.01323 0.00752 -0.1956 0.5875 0.0406 -7.500 0.1437 0.01279 0.00696 -0.1959 0.5775 0.0410 -7.250 0.1720 0.01248 0.00658 -0.1961 0.5687 0.0413 -7.000 0.2001 0.01227 0.00628 -0.1962 0.5607 0.0415 -6.750 0.2287 0.01208 0.00603 -0.1964 0.5531 0.0418 -6.500 0.2568 0.01193 0.00580 -0.1965 0.5453 0.0421 -6.250 0.2856 0.01177 0.00559 -0.1966 0.5394 0.0424 -6.000 0.3142 0.01162 0.00539 -0.1968 0.5335 0.0427 -5.750 0.3424 0.01151 0.00520 -0.1968 0.5274 0.0430 -5.500 0.3713 0.01136 0.00501 -0.1970 0.5227 0.0433 -5.250 0.4000 0.01123 0.00483 -0.1971 0.5177 0.0437 -5.000 0.4284 0.01113 0.00467 -0.1972 0.5127 0.0441 -4.750 0.4568 0.01105 0.00453 -0.1973 0.5080 0.0445 -4.500 0.4857 0.01094 0.00439 -0.1974 0.5040 0.0450 -4.250 0.5144 0.01085 0.00425 -0.1975 0.4994 0.0453 -4.000 0.5427 0.01078 0.00413 -0.1976 0.4948 0.0456 -3.750 0.5710 0.01072 0.00402 -0.1976 0.4909 0.0459 -3.500 0.5999 0.01065 0.00392 -0.1978 0.4879 0.0461 -3.250 0.6287 0.01053 0.00377 -0.1980 0.4846 0.0466 -3.000 0.6573 0.01042 0.00363 -0.1981 0.4808 0.0473 -2.750 0.6854 0.01039 0.00356 -0.1981 0.4767 0.0479 -2.500 0.7136 0.01036 0.00351 -0.1982 0.4734 0.0485 -2.250 0.7423 0.01032 0.00346 -0.1983 0.4709 0.0491 -2.000 0.7708 0.01029 0.00342 -0.1984 0.4679 0.0498 -1.750 0.7990 0.01028 0.00339 -0.1984 0.4643 0.0505 -1.500 0.8267 0.01030 0.00337 -0.1984 0.4605 0.0512 -1.250 0.8542 0.01034 0.00337 -0.1983 0.4566 0.0520 -1.000 0.8825 0.01033 0.00336 -0.1984 0.4542 0.0526 -0.750 0.9107 0.01033 0.00335 -0.1984 0.4513 0.0533 -0.500 0.9386 0.01032 0.00333 -0.1985 0.4481 0.0547 -0.250 0.9660 0.01035 0.00334 -0.1984 0.4444 0.0560 0.000 0.9928 0.01041 0.00338 -0.1982 0.4405 0.0573 0.250 1.0204 0.01044 0.00341 -0.1982 0.4375 0.0586 0.500 1.0479 0.01048 0.00344 -0.1982 0.4340 0.0600 0.750 1.0749 0.01054 0.00349 -0.1980 0.4304 0.0616 1.000 1.1015 0.01060 0.00355 -0.1978 0.4267 0.0653 1.250 1.1275 0.01069 0.00363 -0.1976 0.4230 0.0691 1.500 1.1546 0.01072 0.00368 -0.1975 0.4203 0.0769 1.750 1.1816 0.01070 0.00378 -0.1975 0.4168 0.1224 2.000 1.2076 0.01075 0.00388 -0.1973 0.4127 0.1502 2.250 1.2326 0.01087 0.00400 -0.1968 0.4081 0.1680 2.500 1.2583 0.01092 0.00412 -0.1966 0.4045 0.2004 2.750 1.2844 0.01088 0.00428 -0.1965 0.4005 0.2912 3.000 1.3091 0.01099 0.00444 -0.1961 0.3964 0.3304 3.250 1.3327 0.01115 0.00460 -0.1954 0.3922 0.3483 3.500 1.3567 0.01129 0.00476 -0.1948 0.3887 0.3672 3.750 1.3805 0.01141 0.00491 -0.1942 0.3852 0.3819 4.000 1.4022 0.01155 0.00507 -0.1932 0.3813 0.3953 4.500 1.4423 0.01193 0.00545 -0.1906 0.3735 0.4152 4.750 1.4639 0.01208 0.00565 -0.1896 0.3700 0.4292 5.250 1.5038 0.01251 0.00614 -0.1871 0.3616 0.4703 5.500 1.5226 0.01272 0.00648 -0.1858 0.3577 0.5444 5.750 1.5435 0.01289 0.00675 -0.1848 0.3549 0.5946 6.000 1.5635 0.01309 0.00704 -0.1837 0.3517 0.6390 6.500 1.5996 0.01327 0.00776 -0.1809 0.3448 1.0000 6.750 1.6171 0.01365 0.00814 -0.1795 0.3415 1.0000 7.000 1.6365 0.01397 0.00847 -0.1784 0.3383 1.0000 7.250 1.6546 0.01435 0.00885 -0.1772 0.3347 1.0000 7.500 1.6708 0.01483 0.00932 -0.1757 0.3304 1.0000 7.750 1.6852 0.01540 0.00986 -0.1740 0.3260 1.0000 8.000 1.7029 0.01585 0.01032 -0.1728 0.3219 1.0000 8.250 1.7175 0.01645 0.01091 -0.1713 0.3162 1.0000 8.500 1.7299 0.01720 0.01163 -0.1695 0.3109 1.0000 8.750 1.7459 0.01778 0.01223 -0.1682 0.3072 1.0000 9.000 1.7601 0.01849 0.01294 -0.1668 0.3017 1.0000 9.250 1.7716 0.01937 0.01381 -0.1652 0.2965 1.0000 9.500 1.7852 0.02016 0.01461 -0.1638 0.2927 1.0000 9.750 1.7991 0.02096 0.01542 -0.1626 0.2876 1.0000 10.000 1.8102 0.02196 0.01642 -0.1611 0.2823 1.0000 10.250 1.8206 0.02303 0.01748 -0.1596 0.2774 1.0000 10.500 1.8320 0.02406 0.01852 -0.1582 0.2712 1.0000 10.750 1.8390 0.02542 0.01986 -0.1565 0.2646 1.0000 11.000 1.8486 0.02663 0.02108 -0.1551 0.2580 1.0000 11.250 1.8504 0.02843 0.02285 -0.1531 0.2484 1.0000 11.500 1.8552 0.03008 0.02448 -0.1515 0.2385 1.0000 11.750 1.8511 0.03250 0.02683 -0.1493 0.2240 1.0000 12.000 1.8449 0.03519 0.02947 -0.1471 0.2093 1.0000 12.250 1.8300 0.03881 0.03301 -0.1446 0.1910 1.0000 12.500 1.8161 0.04256 0.03670 -0.1424 0.1748 1.0000 12.750 1.8042 0.04632 0.04044 -0.1407 0.1618 1.0000 13.000 1.7936 0.05014 0.04424 -0.1393 0.1509 1.0000 13.250 1.7855 0.05383 0.04793 -0.1382 0.1413 1.0000 13.500 1.7743 0.05803 0.05213 -0.1372 0.1303 1.0000 13.750 1.7594 0.06282 0.05690 -0.1364 0.1179 1.0000 14.000 1.7313 0.06948 0.06351 -0.1357 0.0996 1.0000 14.250 1.7014 0.07670 0.07069 -0.1354 0.0794 1.0000 14.500 1.6717 0.08420 0.07818 -0.1355 0.0601 1.0000