GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 500,000 Max Cl/Cd: 101.67 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe441-il-500000-n5.txt Download as CSV file: xf-goe441-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2803 0.02798 0.02346 -0.1674 0.7726 0.0286
-10.250 -0.2476 0.02482 0.02004 -0.1752 0.7642 0.0288
-10.000 -0.2184 0.02318 0.01820 -0.1787 0.7568 0.0290
-9.750 -0.1890 0.02187 0.01675 -0.1813 0.7497 0.0292
-9.500 -0.1599 0.02078 0.01550 -0.1833 0.7424 0.0295
-9.250 -0.1306 0.01984 0.01440 -0.1849 0.7356 0.0298
-9.000 -0.1012 0.01901 0.01343 -0.1863 0.7272 0.0301
-8.500 -0.0425 0.01760 0.01172 -0.1886 0.7107 0.0309
-8.250 -0.0132 0.01699 0.01095 -0.1894 0.7014 0.0312
-8.000 0.0163 0.01641 0.01025 -0.1903 0.6913 0.0315
-7.750 0.0454 0.01593 0.00960 -0.1909 0.6794 0.0317
-7.500 0.0748 0.01543 0.00898 -0.1916 0.6650 0.0320
-7.250 0.1036 0.01498 0.00841 -0.1921 0.6448 0.0324
-7.000 0.1306 0.01473 0.00796 -0.1922 0.6025 0.0328
-6.750 0.1559 0.01470 0.00762 -0.1920 0.5560 0.0332
-6.500 0.1836 0.01455 0.00730 -0.1922 0.5362 0.0336
-6.250 0.2124 0.01435 0.00699 -0.1925 0.5250 0.0341
-6.000 0.2412 0.01416 0.00669 -0.1928 0.5166 0.0347
-5.750 0.2707 0.01395 0.00640 -0.1932 0.5102 0.0353
-5.500 0.2999 0.01379 0.00613 -0.1935 0.5040 0.0359
-5.250 0.3290 0.01361 0.00588 -0.1939 0.4982 0.0365
-5.000 0.3588 0.01341 0.00565 -0.1943 0.4938 0.0375
-4.750 0.3882 0.01327 0.00546 -0.1946 0.4891 0.0385
-4.500 0.4175 0.01316 0.00529 -0.1949 0.4849 0.0397
-4.250 0.4465 0.01308 0.00513 -0.1951 0.4809 0.0408
-4.000 0.4760 0.01294 0.00497 -0.1954 0.4775 0.0423
-3.750 0.5056 0.01282 0.00483 -0.1958 0.4745 0.0441
-3.500 0.5351 0.01273 0.00470 -0.1960 0.4710 0.0461
-3.250 0.5644 0.01264 0.00459 -0.1963 0.4673 0.0489
-3.000 0.5933 0.01259 0.00451 -0.1965 0.4637 0.0524
-2.750 0.6221 0.01257 0.00445 -0.1967 0.4603 0.0575
-2.500 0.6512 0.01252 0.00441 -0.1969 0.4576 0.0643
-2.250 0.6804 0.01248 0.00441 -0.1971 0.4552 0.0726
-2.000 0.7093 0.01248 0.00442 -0.1972 0.4524 0.0804
-1.750 0.7378 0.01251 0.00444 -0.1973 0.4493 0.0870
-1.500 0.7662 0.01255 0.00446 -0.1974 0.4461 0.0921
-1.250 0.7942 0.01262 0.00449 -0.1973 0.4430 0.0971
-1.000 0.8222 0.01268 0.00452 -0.1973 0.4400 0.1013
-0.750 0.8508 0.01270 0.00454 -0.1975 0.4379 0.1061
-0.500 0.8793 0.01273 0.00457 -0.1975 0.4356 0.1106
-0.250 0.9079 0.01273 0.00459 -0.1977 0.4328 0.1163
0.000 0.9361 0.01277 0.00462 -0.1977 0.4298 0.1207
0.250 0.9639 0.01283 0.00466 -0.1977 0.4269 0.1257
0.500 0.9916 0.01289 0.00473 -0.1977 0.4242 0.1338
0.750 1.0190 0.01297 0.00482 -0.1977 0.4216 0.1457
1.000 1.0471 0.01299 0.00493 -0.1978 0.4194 0.1736
1.250 1.0751 0.01304 0.00502 -0.1978 0.4168 0.1967
1.500 1.1027 0.01310 0.00512 -0.1978 0.4141 0.2128
1.750 1.1300 0.01318 0.00523 -0.1977 0.4114 0.2279
2.000 1.1570 0.01327 0.00534 -0.1976 0.4086 0.2470
2.250 1.1838 0.01335 0.00548 -0.1975 0.4058 0.2805
2.500 1.2105 0.01341 0.00570 -0.1975 0.4030 0.3608
2.750 1.2377 0.01348 0.00587 -0.1974 0.4007 0.4020
3.000 1.2644 0.01358 0.00603 -0.1973 0.3981 0.4302
3.250 1.2905 0.01371 0.00619 -0.1970 0.3950 0.4531
3.500 1.3161 0.01385 0.00637 -0.1966 0.3919 0.4752
3.750 1.3410 0.01403 0.00656 -0.1962 0.3889 0.4949
4.000 1.3651 0.01423 0.00677 -0.1956 0.3858 0.5133
4.500 1.4162 0.01449 0.00716 -0.1949 0.3807 0.5547
4.750 1.4410 0.01463 0.00739 -0.1945 0.3780 0.5879
5.000 1.4650 0.01476 0.00765 -0.1939 0.3753 0.6372
5.250 1.4869 0.01488 0.00794 -0.1929 0.3724 0.7195
5.500 1.5060 0.01492 0.00820 -0.1913 0.3696 0.8332
5.750 1.5240 0.01499 0.00838 -0.1894 0.3672 1.0000
6.000 1.5471 0.01523 0.00863 -0.1887 0.3645 1.0000
6.250 1.5694 0.01549 0.00890 -0.1878 0.3618 1.0000
6.500 1.5911 0.01579 0.00920 -0.1869 0.3590 1.0000
6.750 1.6119 0.01612 0.00952 -0.1859 0.3562 1.0000
7.000 1.6318 0.01650 0.00988 -0.1847 0.3535 1.0000
7.250 1.6531 0.01682 0.01023 -0.1838 0.3511 1.0000
7.500 1.6747 0.01713 0.01057 -0.1830 0.3484 1.0000
7.750 1.6953 0.01749 0.01095 -0.1820 0.3452 1.0000
8.000 1.7147 0.01790 0.01137 -0.1808 0.3418 1.0000
8.250 1.7328 0.01838 0.01184 -0.1795 0.3386 1.0000
8.500 1.7514 0.01885 0.01233 -0.1783 0.3351 1.0000
8.750 1.7710 0.01927 0.01279 -0.1773 0.3308 1.0000
9.000 1.7885 0.01980 0.01334 -0.1760 0.3262 1.0000
9.250 1.8037 0.02046 0.01398 -0.1745 0.3216 1.0000
9.500 1.8215 0.02101 0.01456 -0.1733 0.3167 1.0000
9.750 1.8376 0.02165 0.01522 -0.1720 0.3110 1.0000
10.000 1.8504 0.02251 0.01607 -0.1703 0.3056 1.0000
10.250 1.8665 0.02319 0.01678 -0.1690 0.2995 1.0000
10.500 1.8782 0.02416 0.01774 -0.1673 0.2923 1.0000
10.750 1.8907 0.02510 0.01869 -0.1658 0.2859 1.0000
11.000 1.9025 0.02612 0.01973 -0.1642 0.2793 1.0000
11.250 1.9115 0.02735 0.02096 -0.1624 0.2730 1.0000
11.500 1.9230 0.02844 0.02208 -0.1609 0.2664 1.0000
12.000 1.9360 0.03144 0.02509 -0.1573 0.2507 1.0000
12.250 1.9388 0.03330 0.02695 -0.1553 0.2432 1.0000
12.500 1.9456 0.03490 0.02858 -0.1537 0.2361 1.0000
12.750 1.9466 0.03704 0.03073 -0.1518 0.2292 1.0000
13.000 1.9504 0.03900 0.03272 -0.1503 0.2220 1.0000
13.250 1.9474 0.04166 0.03539 -0.1484 0.2141 1.0000
13.500 1.9461 0.04424 0.03799 -0.1468 0.2049 1.0000
13.750 1.9379 0.04757 0.04133 -0.1449 0.1951 1.0000
14.000 1.9253 0.05150 0.04526 -0.1432 0.1838 1.0000
14.250 1.9096 0.05594 0.04971 -0.1415 0.1715 1.0000
14.500 1.8904 0.06094 0.05472 -0.1401 0.1589 1.0000
14.750 1.8643 0.06705 0.06085 -0.1389 0.1452 1.0000
15.000 1.8327 0.07415 0.06797 -0.1381 0.1316 1.0000
15.250 1.8055 0.08086 0.07473 -0.1377 0.1219 1.0000
15.500 1.7801 0.08743 0.08135 -0.1375 0.1131 1.0000
15.750 1.7572 0.09367 0.08765 -0.1375 0.1054 1.0000
16.000 1.7348 0.09990 0.09392 -0.1376 0.0973 1.0000
16.250 1.7046 0.10735 0.10137 -0.1381 0.0811 1.0000
16.500 1.6733 0.11507 0.10907 -0.1389 0.0620 1.0000
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