XFOIL Version 6.96 Calculated polar for: GOE 226 (MVA H.36) 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 ------ -------- --------- --------- -------- -------- -------- -12.250 -0.1360 0.11503 0.11194 -0.0750 0.8489 0.0227 -12.000 -0.1254 0.11291 0.10980 -0.0760 0.8437 0.0230 -10.500 -0.3112 0.02787 0.02373 -0.1662 0.8126 0.0328 -10.250 -0.2681 0.02289 0.01837 -0.1791 0.8072 0.0334 -10.000 -0.2343 0.02095 0.01615 -0.1837 0.8018 0.0339 -9.750 -0.2023 0.01962 0.01461 -0.1866 0.7952 0.0343 -9.500 -0.1718 0.01855 0.01344 -0.1886 0.7889 0.0348 -9.250 -0.1414 0.01778 0.01256 -0.1901 0.7835 0.0352 -9.000 -0.1111 0.01712 0.01181 -0.1914 0.7770 0.0357 -8.750 -0.0812 0.01656 0.01113 -0.1924 0.7700 0.0363 -8.500 -0.0512 0.01602 0.01050 -0.1933 0.7624 0.0369 -8.250 -0.0213 0.01550 0.00984 -0.1941 0.7547 0.0376 -8.000 0.0088 0.01499 0.00920 -0.1950 0.7483 0.0382 -7.750 0.0388 0.01453 0.00861 -0.1957 0.7413 0.0388 -7.250 0.0986 0.01364 0.00754 -0.1971 0.7271 0.0401 -7.000 0.1283 0.01332 0.00714 -0.1976 0.7194 0.0408 -6.750 0.1580 0.01303 0.00677 -0.1980 0.7123 0.0416 -6.500 0.1877 0.01277 0.00642 -0.1985 0.7046 0.0426 -6.250 0.2173 0.01254 0.00609 -0.1988 0.6976 0.0436 -6.000 0.2470 0.01232 0.00577 -0.1992 0.6906 0.0445 -5.750 0.2767 0.01202 0.00541 -0.1997 0.6844 0.0456 -5.500 0.3065 0.01180 0.00515 -0.2001 0.6784 0.0467 -5.250 0.3361 0.01163 0.00491 -0.2004 0.6720 0.0480 -4.750 0.3951 0.01135 0.00447 -0.2010 0.6601 0.0506 -4.500 0.4247 0.01115 0.00424 -0.2014 0.6536 0.0525 -4.000 0.4837 0.01092 0.00391 -0.2019 0.6438 0.0565 -3.750 0.5133 0.01081 0.00375 -0.2022 0.6386 0.0585 -3.500 0.5425 0.01072 0.00362 -0.2024 0.6327 0.0612 -3.250 0.5718 0.01065 0.00350 -0.2026 0.6275 0.0643 -3.000 0.6012 0.01056 0.00342 -0.2029 0.6223 0.0684 -2.750 0.6303 0.01052 0.00335 -0.2030 0.6171 0.0735 -2.500 0.6592 0.01050 0.00331 -0.2032 0.6124 0.0799 -2.250 0.6886 0.01045 0.00328 -0.2034 0.6077 0.0868 -2.000 0.7175 0.01044 0.00325 -0.2035 0.6020 0.0936 -1.750 0.7461 0.01045 0.00322 -0.2036 0.5959 0.0993 -1.500 0.7750 0.01044 0.00320 -0.2037 0.5900 0.1052 -1.250 0.8037 0.01044 0.00318 -0.2038 0.5832 0.1100 -1.000 0.8320 0.01046 0.00317 -0.2039 0.5765 0.1158 -0.750 0.8608 0.01046 0.00317 -0.2040 0.5690 0.1214 -0.500 0.8887 0.01049 0.00317 -0.2040 0.5601 0.1288 -0.250 0.9171 0.01051 0.00319 -0.2040 0.5497 0.1379 0.000 0.9447 0.01053 0.00324 -0.2040 0.5370 0.1597 0.250 0.9718 0.01059 0.00332 -0.2039 0.5192 0.1992 0.500 0.9972 0.01078 0.00346 -0.2035 0.4948 0.2290 0.750 1.0219 0.01105 0.00363 -0.2030 0.4726 0.2485 1.000 1.0469 0.01132 0.00381 -0.2025 0.4575 0.2620 1.250 1.0727 0.01153 0.00398 -0.2021 0.4473 0.2743 1.500 1.0985 0.01173 0.00415 -0.2018 0.4398 0.2857 1.750 1.1245 0.01193 0.00432 -0.2014 0.4328 0.2972 2.000 1.1496 0.01217 0.00453 -0.2010 0.4259 0.3112 2.250 1.1758 0.01233 0.00471 -0.2007 0.4205 0.3240 2.500 1.2015 0.01251 0.00490 -0.2003 0.4152 0.3364 2.750 1.2265 0.01274 0.00511 -0.1999 0.4102 0.3493 3.000 1.2517 0.01294 0.00533 -0.1994 0.4055 0.3646 3.250 1.2776 0.01309 0.00552 -0.1991 0.4012 0.3791 3.500 1.3029 0.01327 0.00573 -0.1987 0.3974 0.3949 3.750 1.3278 0.01347 0.00596 -0.1982 0.3944 0.4131 4.000 1.3522 0.01369 0.00621 -0.1977 0.3915 0.4343 4.250 1.3761 0.01392 0.00648 -0.1971 0.3887 0.4577 4.500 1.4015 0.01406 0.00670 -0.1967 0.3867 0.4799 4.750 1.4264 0.01422 0.00693 -0.1962 0.3843 0.4983 5.000 1.4507 0.01440 0.00719 -0.1957 0.3816 0.5194 5.250 1.4743 0.01460 0.00746 -0.1950 0.3786 0.5449 5.500 1.4970 0.01484 0.00777 -0.1943 0.3754 0.5773 5.750 1.5180 0.01509 0.00812 -0.1932 0.3723 0.6254 6.000 1.5385 0.01530 0.00843 -0.1920 0.3699 0.6760 6.250 1.5613 0.01531 0.00873 -0.1912 0.3675 0.7805 6.500 1.5792 0.01538 0.00897 -0.1894 0.3648 1.0000 6.750 1.6000 0.01570 0.00931 -0.1883 0.3611 1.0000 7.000 1.6192 0.01609 0.00970 -0.1870 0.3570 1.0000 7.250 1.6376 0.01654 0.01013 -0.1856 0.3529 1.0000 7.500 1.6588 0.01685 0.01049 -0.1847 0.3490 1.0000 7.750 1.6784 0.01725 0.01092 -0.1836 0.3445 1.0000 8.000 1.6962 0.01775 0.01142 -0.1822 0.3397 1.0000 8.250 1.7139 0.01827 0.01195 -0.1809 0.3352 1.0000 8.500 1.7333 0.01871 0.01244 -0.1798 0.3302 1.0000 8.750 1.7493 0.01935 0.01308 -0.1783 0.3232 1.0000 9.000 1.7657 0.01997 0.01371 -0.1770 0.3158 1.0000 9.250 1.7804 0.02072 0.01445 -0.1754 0.3074 1.0000 9.500 1.7954 0.02147 0.01522 -0.1739 0.2996 1.0000 9.750 1.8075 0.02241 0.01615 -0.1722 0.2904 1.0000 10.000 1.8194 0.02340 0.01712 -0.1704 0.2799 1.0000 10.250 1.8282 0.02461 0.01830 -0.1684 0.2684 1.0000 10.500 1.8347 0.02602 0.01966 -0.1662 0.2560 1.0000 10.750 1.8389 0.02762 0.02121 -0.1638 0.2434 1.0000 11.000 1.8452 0.02912 0.02268 -0.1618 0.2324 1.0000 11.250 1.8515 0.03064 0.02420 -0.1598 0.2236 1.0000 11.500 1.8556 0.03237 0.02591 -0.1577 0.2144 1.0000 11.750 1.8617 0.03397 0.02753 -0.1558 0.2059 1.0000 12.000 1.8640 0.03595 0.02949 -0.1538 0.1970 1.0000 12.250 1.8684 0.03779 0.03134 -0.1520 0.1866 1.0000 12.500 1.8682 0.04012 0.03364 -0.1500 0.1733 1.0000 12.750 1.8613 0.04317 0.03661 -0.1478 0.1536 1.0000 13.250 1.8333 0.05108 0.04432 -0.1431 0.1107 1.0000 13.500 1.8192 0.05530 0.04849 -0.1412 0.0948 1.0000 13.750 1.7977 0.06048 0.05359 -0.1393 0.0726 1.0000 14.000 1.7716 0.06644 0.05946 -0.1376 0.0501 1.0000 14.250 1.7583 0.07103 0.06407 -0.1365 0.0419 1.0000 14.500 1.7505 0.07502 0.06811 -0.1357 0.0379 1.0000 14.750 1.7447 0.07886 0.07203 -0.1350 0.0356 1.0000 15.000 1.7393 0.08271 0.07596 -0.1345 0.0338 1.0000 15.250 1.7330 0.08672 0.08005 -0.1341 0.0323 1.0000 15.500 1.7276 0.09064 0.08406 -0.1338 0.0312 1.0000 15.750 1.7229 0.09453 0.08805 -0.1337 0.0302 1.0000 16.000 1.7169 0.09867 0.09228 -0.1336 0.0292 1.0000 16.250 1.7099 0.10300 0.09670 -0.1338 0.0284 1.0000 16.500 1.7023 0.10747 0.10126 -0.1341 0.0276 1.0000