XFOIL Version 6.96 Calculated polar for: GOE 222 (MVA H.33) 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -0.5248 0.12101 0.11855 -0.1003 0.9683 0.0175 -19.250 -0.5437 0.11402 0.11145 -0.1042 0.9656 0.0178 -19.000 -0.5581 0.10798 0.10531 -0.1076 0.9624 0.0181 -18.750 -0.5684 0.10275 0.09998 -0.1105 0.9591 0.0183 -18.500 -0.5757 0.09812 0.09526 -0.1130 0.9561 0.0185 -18.250 -0.5826 0.09348 0.09054 -0.1157 0.9532 0.0187 -18.000 -0.5876 0.08928 0.08626 -0.1181 0.9495 0.0188 -17.750 -0.5924 0.08521 0.08214 -0.1204 0.9456 0.0191 -17.500 -0.5973 0.08116 0.07801 -0.1227 0.9419 0.0192 -17.250 -0.5985 0.07760 0.07440 -0.1249 0.9385 0.0194 -17.000 -0.6005 0.07391 0.07067 -0.1272 0.9343 0.0196 -16.750 -0.6002 0.07065 0.06735 -0.1291 0.9298 0.0198 -16.500 -0.6007 0.06734 0.06397 -0.1311 0.9257 0.0200 -16.250 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0.00457 -0.2008 0.6780 0.0333 -6.250 0.2080 0.01065 0.00437 -0.2014 0.6753 0.0340 -6.000 0.2375 0.01051 0.00419 -0.2018 0.6724 0.0346 -5.750 0.2670 0.01039 0.00403 -0.2023 0.6695 0.0352 -5.500 0.2973 0.01021 0.00384 -0.2029 0.6675 0.0362 -5.250 0.3274 0.01005 0.00368 -0.2035 0.6652 0.0375 -5.000 0.3574 0.00992 0.00354 -0.2040 0.6628 0.0389 -4.750 0.3872 0.00981 0.00342 -0.2045 0.6599 0.0404 -4.500 0.4167 0.00970 0.00329 -0.2050 0.6567 0.0429 -4.250 0.4460 0.00960 0.00317 -0.2053 0.6536 0.0463 -4.000 0.4758 0.00949 0.00305 -0.2058 0.6510 0.0514 -3.750 0.5066 0.00915 0.00285 -0.2068 0.6483 0.0911 -3.500 0.5367 0.00895 0.00273 -0.2074 0.6449 0.1173 -3.250 0.5666 0.00875 0.00260 -0.2081 0.6410 0.1472 -3.000 0.5962 0.00847 0.00247 -0.2088 0.6368 0.2001 -2.750 0.6257 0.00835 0.00244 -0.2093 0.6329 0.2327 -2.500 0.6552 0.00830 0.00243 -0.2097 0.6278 0.2519 -2.250 0.6837 0.00829 0.00244 -0.2099 0.6213 0.2655 -2.000 0.7120 0.00832 0.00244 -0.2101 0.6146 0.2745 -1.750 0.7393 0.00837 0.00246 -0.2100 0.6027 0.2824 -1.500 0.7648 0.00849 0.00251 -0.2096 0.5831 0.2910 -1.000 0.8094 0.00905 0.00279 -0.2075 0.5257 0.3051 -0.750 0.8330 0.00929 0.00292 -0.2068 0.5070 0.3089 -0.500 0.8574 0.00950 0.00305 -0.2062 0.4925 0.3122 -0.250 0.8818 0.00969 0.00318 -0.2057 0.4798 0.3155 0.000 0.9056 0.00991 0.00333 -0.2050 0.4671 0.3185 0.250 0.9304 0.01007 0.00345 -0.2045 0.4569 0.3217 0.500 0.9545 0.01026 0.00358 -0.2038 0.4488 0.3253 0.750 0.9793 0.01038 0.00368 -0.2033 0.4435 0.3285 1.000 1.0027 0.01050 0.00380 -0.2025 0.4381 0.3328 1.250 1.0247 0.01066 0.00394 -0.2015 0.4329 0.3361 1.500 1.0484 0.01078 0.00407 -0.2008 0.4292 0.3392 1.750 1.0729 0.01092 0.00420 -0.2002 0.4254 0.3422 2.000 1.0974 0.01108 0.00435 -0.1997 0.4216 0.3447 2.250 1.1212 0.01128 0.00453 -0.1991 0.4173 0.3473 2.500 1.1451 0.01148 0.00472 -0.1985 0.4126 0.3508 2.750 1.1698 0.01164 0.00490 -0.1981 0.4083 0.3545 3.000 1.1937 0.01184 0.00510 -0.1975 0.4041 0.3584 3.250 1.2170 0.01206 0.00531 -0.1968 0.4006 0.3619 3.500 1.2400 0.01229 0.00553 -0.1961 0.3974 0.3646 3.750 1.2641 0.01247 0.00574 -0.1957 0.3950 0.3685 4.000 1.2883 0.01265 0.00595 -0.1952 0.3927 0.3724 4.250 1.3119 0.01286 0.00618 -0.1946 0.3896 0.3762 4.500 1.3347 0.01310 0.00643 -0.1939 0.3861 0.3798 4.750 1.3569 0.01336 0.00670 -0.1932 0.3829 0.3833 5.000 1.3782 0.01367 0.00702 -0.1923 0.3793 0.3882 5.250 1.4012 0.01390 0.00729 -0.1917 0.3764 0.3932 5.500 1.4239 0.01416 0.00757 -0.1910 0.3728 0.3974 6.000 1.4664 0.01480 0.00824 -0.1893 0.3649 0.4063 6.250 1.4866 0.01517 0.00863 -0.1883 0.3614 0.4116 6.500 1.5087 0.01545 0.00896 -0.1876 0.3579 0.4174 6.750 1.5297 0.01580 0.00933 -0.1868 0.3527 0.4243 7.000 1.5471 0.01632 0.00984 -0.1854 0.3459 0.4317 7.500 1.5838 0.01730 0.01085 -0.1830 0.3304 0.4475 7.750 1.5981 0.01801 0.01152 -0.1813 0.3161 0.4564 8.000 1.6065 0.01906 0.01248 -0.1787 0.2929 0.4672 8.250 1.6086 0.02050 0.01379 -0.1754 0.2661 0.4788 8.500 1.6136 0.02184 0.01506 -0.1725 0.2461 0.4936 8.750 1.6204 0.02310 0.01628 -0.1700 0.2310 0.5105 9.000 1.6281 0.02436 0.01752 -0.1678 0.2194 0.5264 9.250 1.6413 0.02530 0.01849 -0.1663 0.2130 0.5418 9.500 1.6520 0.02645 0.01964 -0.1645 0.2063 0.5558 9.750 1.6653 0.02744 0.02067 -0.1632 0.2012 0.5702 10.000 1.6789 0.02843 0.02170 -0.1619 0.1970 0.5856 10.250 1.6914 0.02951 0.02283 -0.1605 0.1928 0.6028 10.500 1.7029 0.03072 0.02409 -0.1592 0.1884 0.6220 10.750 1.7180 0.03167 0.02514 -0.1583 0.1858 0.6522 11.000 1.7309 0.03227 0.02630 -0.1569 0.1826 1.0000 11.250 1.7426 0.03351 0.02754 -0.1557 0.1782 1.0000 11.500 1.7510 0.03504 0.02907 -0.1541 0.1731 1.0000 11.750 1.7628 0.03629 0.03034 -0.1530 0.1687 1.0000 12.000 1.7701 0.03796 0.03199 -0.1515 0.1613 1.0000 12.250 1.7774 0.03964 0.03367 -0.1500 0.1544 1.0000 12.500 1.7804 0.04172 0.03571 -0.1482 0.1440 1.0000 12.750 1.7782 0.04429 0.03822 -0.1462 0.1308 1.0000 13.000 1.7742 0.04708 0.04095 -0.1441 0.1182 1.0000 13.250 1.7692 0.05002 0.04385 -0.1420 0.1060 1.0000 13.500 1.7595 0.05348 0.04726 -0.1398 0.0910 1.0000 13.750 1.7321 0.05879 0.05243 -0.1366 0.0620 1.0000 14.000 1.7198 0.06278 0.05640 -0.1347 0.0505 1.0000 14.250 1.7164 0.06593 0.05959 -0.1334 0.0459 1.0000 14.500 1.7171 0.06863 0.06233 -0.1323 0.0424 1.0000 14.750 1.7140 0.07182 0.06556 -0.1312 0.0383 1.0000 15.000 1.7113 0.07503 0.06880 -0.1303 0.0337 1.0000 15.250 1.7041 0.07882 0.07260 -0.1293 0.0259 1.0000 15.500 1.6915 0.08333 0.07710 -0.1283 0.0173 1.0000 15.750 1.6877 0.08682 0.08063 -0.1276 0.0151 1.0000