GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 421 AIRFOIL (goe421-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.93 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe421-il-1000000.txt Download as CSV file: xf-goe421-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 421 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.3634 0.10053 0.09808 -0.1416 0.9761 0.0262
-18.000 -0.3940 0.09217 0.08957 -0.1465 0.9733 0.0265
-17.750 -0.4125 0.08600 0.08329 -0.1500 0.9704 0.0268
-17.500 -0.4162 0.08253 0.07979 -0.1519 0.9673 0.0273
-17.250 -0.4208 0.07896 0.07620 -0.1536 0.9636 0.0277
-17.000 -0.4280 0.07494 0.07214 -0.1557 0.9596 0.0281
-16.750 -0.4332 0.07136 0.06851 -0.1575 0.9558 0.0284
-16.500 -0.4418 0.06723 0.06432 -0.1598 0.9518 0.0287
-16.250 -0.4474 0.06354 0.06058 -0.1619 0.9472 0.0291
-16.000 -0.4578 0.05934 0.05630 -0.1643 0.9424 0.0294
-15.750 -0.4670 0.05538 0.05226 -0.1668 0.9374 0.0297
-15.500 -0.4795 0.05110 0.04790 -0.1697 0.9315 0.0300
-15.250 -0.4933 0.04667 0.04337 -0.1726 0.9252 0.0302
-15.000 -0.5076 0.04207 0.03866 -0.1761 0.9180 0.0304
-14.750 -0.5225 0.03717 0.03364 -0.1800 0.9096 0.0306
-14.500 -0.5398 0.03138 0.02771 -0.1860 0.8995 0.0307
-14.250 -0.5451 0.02391 0.01993 -0.1974 0.8898 0.0311
-14.000 -0.5341 0.02184 0.01776 -0.1991 0.8820 0.0317
-13.750 -0.5155 0.02072 0.01654 -0.1997 0.8756 0.0323
-13.500 -0.4950 0.01991 0.01567 -0.2000 0.8690 0.0328
-13.250 -0.4731 0.01921 0.01488 -0.2002 0.8624 0.0334
-13.000 -0.4504 0.01860 0.01418 -0.2003 0.8564 0.0340
-12.750 -0.4270 0.01807 0.01357 -0.2003 0.8500 0.0346
-12.500 -0.4025 0.01765 0.01303 -0.2004 0.8439 0.0351
-12.250 -0.3820 0.01684 0.01215 -0.2002 0.8377 0.0358
-12.000 -0.3596 0.01622 0.01147 -0.2000 0.8312 0.0366
-11.750 -0.3351 0.01582 0.01099 -0.2000 0.8252 0.0373
-11.500 -0.3100 0.01546 0.01059 -0.1999 0.8198 0.0380
-11.250 -0.2846 0.01513 0.01019 -0.1998 0.8141 0.0388
-11.000 -0.2591 0.01484 0.00980 -0.1997 0.8086 0.0395
-10.750 -0.2331 0.01455 0.00945 -0.1996 0.8035 0.0400
-10.500 -0.2102 0.01396 0.00880 -0.1993 0.7977 0.0410
-10.250 -0.1852 0.01362 0.00839 -0.1991 0.7920 0.0420
-10.000 -0.1592 0.01333 0.00808 -0.1990 0.7873 0.0429
-9.750 -0.1331 0.01307 0.00776 -0.1989 0.7821 0.0438
-9.500 -0.1069 0.01286 0.00748 -0.1987 0.7770 0.0447
-9.250 -0.0800 0.01269 0.00725 -0.1986 0.7723 0.0454
-9.000 -0.0554 0.01223 0.00675 -0.1984 0.7672 0.0467
-8.750 -0.0297 0.01195 0.00642 -0.1981 0.7619 0.0478
-8.500 -0.0034 0.01177 0.00617 -0.1980 0.7567 0.0490
-8.250 0.0235 0.01157 0.00595 -0.1979 0.7523 0.0502
-8.000 0.0504 0.01142 0.00575 -0.1978 0.7474 0.0513
-7.750 0.0759 0.01114 0.00540 -0.1975 0.7424 0.0528
-7.500 0.1023 0.01091 0.00515 -0.1973 0.7378 0.0545
-7.250 0.1291 0.01073 0.00495 -0.1972 0.7329 0.0560
-7.000 0.1558 0.01061 0.00477 -0.1970 0.7280 0.0575
-6.750 0.1821 0.01046 0.00455 -0.1968 0.7230 0.0595
-6.500 0.2089 0.01024 0.00434 -0.1967 0.7190 0.0620
-6.250 0.2356 0.01011 0.00418 -0.1965 0.7138 0.0642
-6.000 0.2616 0.01003 0.00403 -0.1962 0.7080 0.0662
-5.750 0.2878 0.00984 0.00384 -0.1959 0.7028 0.0699
-5.500 0.3145 0.00973 0.00371 -0.1957 0.6977 0.0732
-5.250 0.3404 0.00959 0.00355 -0.1954 0.6925 0.0783
-5.000 0.3665 0.00953 0.00345 -0.1951 0.6873 0.0833
-4.750 0.3930 0.00935 0.00331 -0.1949 0.6826 0.0918
-4.500 0.4190 0.00921 0.00318 -0.1946 0.6774 0.1023
-4.250 0.4440 0.00910 0.00307 -0.1942 0.6719 0.1177
-4.000 0.4702 0.00890 0.00301 -0.1940 0.6675 0.1502
-3.750 0.4966 0.00888 0.00304 -0.1938 0.6623 0.1700
-3.500 0.5219 0.00892 0.00305 -0.1933 0.6568 0.1783
-3.250 0.5475 0.00898 0.00309 -0.1928 0.6516 0.1854
-3.000 0.5740 0.00903 0.00311 -0.1926 0.6469 0.1892
-2.750 0.5988 0.00903 0.00309 -0.1920 0.6422 0.1940
-2.500 0.6221 0.00908 0.00312 -0.1911 0.6373 0.1983
-2.250 0.6473 0.00911 0.00314 -0.1906 0.6333 0.2017
-2.000 0.6725 0.00914 0.00316 -0.1901 0.6290 0.2043
-1.750 0.6969 0.00921 0.00319 -0.1894 0.6247 0.2063
-1.500 0.7207 0.00927 0.00320 -0.1887 0.6202 0.2086
-1.250 0.7467 0.00925 0.00320 -0.1884 0.6165 0.2122
-1.000 0.7728 0.00927 0.00323 -0.1881 0.6123 0.2153
-0.750 0.7977 0.00933 0.00328 -0.1877 0.6079 0.2188
-0.500 0.8217 0.00946 0.00337 -0.1870 0.6032 0.2223
-0.250 0.8478 0.00953 0.00343 -0.1868 0.5992 0.2241
0.000 0.8742 0.00959 0.00349 -0.1866 0.5948 0.2258
0.250 0.8995 0.00964 0.00353 -0.1863 0.5899 0.2301
0.500 0.9231 0.00976 0.00363 -0.1856 0.5846 0.2332
0.750 0.9493 0.00981 0.00370 -0.1855 0.5801 0.2354
1.000 0.9742 0.00991 0.00379 -0.1851 0.5745 0.2375
1.250 0.9970 0.01007 0.00391 -0.1843 0.5685 0.2395
1.500 1.0222 0.01017 0.00401 -0.1840 0.5632 0.2415
1.750 1.0465 0.01030 0.00412 -0.1835 0.5571 0.2433
2.000 1.0680 0.01049 0.00429 -0.1825 0.5505 0.2471
2.250 1.0929 0.01060 0.00442 -0.1822 0.5445 0.2525
2.500 1.1154 0.01078 0.00460 -0.1814 0.5369 0.2580
2.750 1.1377 0.01097 0.00479 -0.1806 0.5296 0.2653
3.000 1.1599 0.01116 0.00500 -0.1799 0.5208 0.2804
3.250 1.1807 0.01138 0.00529 -0.1789 0.5119 0.3149
3.500 1.2009 0.01165 0.00560 -0.1779 0.5012 0.3579
3.750 1.2216 0.01191 0.00591 -0.1769 0.4902 0.3879
4.000 1.2392 0.01231 0.00629 -0.1754 0.4780 0.4098
4.250 1.2555 0.01277 0.00673 -0.1737 0.4642 0.4304
4.500 1.2729 0.01321 0.00717 -0.1723 0.4500 0.4555
4.750 1.2893 0.01367 0.00768 -0.1707 0.4358 0.4975
5.000 1.3067 0.01399 0.00833 -0.1696 0.4212 0.6725
5.250 1.3160 0.01405 0.00893 -0.1665 0.4079 1.0000
5.500 1.3291 0.01478 0.00957 -0.1645 0.3947 1.0000
5.750 1.3435 0.01546 0.01019 -0.1627 0.3827 1.0000
6.000 1.3595 0.01609 0.01077 -0.1612 0.3733 1.0000
6.250 1.3728 0.01686 0.01147 -0.1594 0.3642 1.0000
6.500 1.3907 0.01743 0.01202 -0.1582 0.3576 1.0000
6.750 1.4062 0.01812 0.01269 -0.1568 0.3517 1.0000
7.000 1.4204 0.01890 0.01343 -0.1552 0.3458 1.0000
7.250 1.4397 0.01942 0.01396 -0.1544 0.3425 1.0000
7.500 1.4565 0.02009 0.01462 -0.1533 0.3387 1.0000
7.750 1.4722 0.02083 0.01536 -0.1521 0.3348 1.0000
8.000 1.4858 0.02172 0.01622 -0.1506 0.3304 1.0000
8.250 1.5031 0.02240 0.01692 -0.1496 0.3279 1.0000
8.500 1.5218 0.02300 0.01754 -0.1489 0.3260 1.0000
8.750 1.5388 0.02371 0.01827 -0.1479 0.3234 1.0000
9.000 1.5540 0.02455 0.01911 -0.1468 0.3201 1.0000
9.250 1.5673 0.02551 0.02006 -0.1454 0.3162 1.0000
9.500 1.5784 0.02665 0.02118 -0.1439 0.3123 1.0000
9.750 1.5980 0.02723 0.02181 -0.1434 0.3100 1.0000
10.000 1.6152 0.02798 0.02258 -0.1426 0.3074 1.0000
10.250 1.6300 0.02890 0.02352 -0.1416 0.3049 1.0000
10.500 1.6438 0.02988 0.02451 -0.1405 0.3020 1.0000
10.750 1.6553 0.03105 0.02568 -0.1391 0.2988 1.0000
11.000 1.6663 0.03226 0.02690 -0.1378 0.2957 1.0000
11.250 1.6846 0.03295 0.02765 -0.1373 0.2938 1.0000
11.500 1.7005 0.03384 0.02857 -0.1366 0.2911 1.0000
11.750 1.7139 0.03492 0.02967 -0.1356 0.2877 1.0000
12.000 1.7250 0.03616 0.03092 -0.1344 0.2838 1.0000
12.250 1.7328 0.03769 0.03245 -0.1330 0.2794 1.0000
12.500 1.7495 0.03852 0.03333 -0.1324 0.2767 1.0000
12.750 1.7630 0.03960 0.03444 -0.1316 0.2727 1.0000
13.000 1.7715 0.04113 0.03598 -0.1303 0.2678 1.0000
13.250 1.7807 0.04259 0.03745 -0.1291 0.2625 1.0000
13.500 1.7893 0.04413 0.03899 -0.1280 0.2541 1.0000
13.750 1.7938 0.04601 0.04084 -0.1265 0.2440 1.0000
14.000 1.7905 0.04859 0.04336 -0.1245 0.2268 1.0000
14.250 1.7601 0.05362 0.04813 -0.1205 0.1866 1.0000
14.500 1.7348 0.05836 0.05273 -0.1171 0.1617 1.0000
14.750 1.7230 0.06197 0.05630 -0.1150 0.1491 1.0000
15.000 1.7171 0.06510 0.05942 -0.1134 0.1402 1.0000
15.250 1.7148 0.06793 0.06225 -0.1121 0.1324 1.0000
15.500 1.7077 0.07130 0.06561 -0.1107 0.1242 1.0000
15.750 1.7044 0.07427 0.06857 -0.1095 0.1155 1.0000
16.000 1.6943 0.07808 0.07236 -0.1082 0.1046 1.0000
16.250 1.6797 0.08248 0.07671 -0.1069 0.0920 1.0000
16.500 1.6597 0.08758 0.08176 -0.1055 0.0777 1.0000
16.750 1.6307 0.09386 0.08798 -0.1042 0.0601 1.0000
17.000 1.5980 0.10083 0.09491 -0.1032 0.0419 1.0000
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