GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il) Reynolds number: 100,000 Max Cl/Cd: 59.7 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe226-il-100000-n5.txt Download as CSV file: xf-goe226-il-100000-n5.csv |
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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.0274 0.10328 0.09779 -0.1022 0.8993 0.0829
-9.250 0.0261 0.10116 0.09566 -0.1053 0.8920 0.0834
-9.000 0.0303 0.09850 0.09300 -0.1072 0.8847 0.0836
-8.750 0.0363 0.09147 0.08590 -0.1083 0.8786 0.0653
-8.500 0.0520 0.08902 0.08342 -0.1081 0.8739 0.0645
-8.250 0.0602 0.08653 0.08093 -0.1087 0.8671 0.0640
-8.000 0.0643 0.08376 0.07815 -0.1102 0.8597 0.0643
-7.750 0.0693 0.08069 0.07505 -0.1120 0.8539 0.0646
-7.500 0.0720 0.07833 0.07271 -0.1126 0.8449 0.0644
-7.250 0.0787 0.07566 0.07001 -0.1137 0.8391 0.0641
-7.000 0.0844 0.07297 0.06733 -0.1153 0.8307 0.0638
-6.750 0.0930 0.06969 0.06402 -0.1180 0.8237 0.0636
-6.500 0.1019 0.06560 0.05989 -0.1227 0.8167 0.0642
-6.250 0.1111 0.05887 0.05309 -0.1325 0.8082 0.0652
-6.000 0.1353 0.05144 0.04553 -0.1440 0.8034 0.0658
-5.750 0.1763 0.03990 0.03360 -0.1661 0.7951 0.0676
-5.500 0.2324 0.03229 0.02511 -0.1830 0.7904 0.0716
-5.250 0.2774 0.02844 0.02045 -0.1902 0.7869 0.0743
-5.000 0.3036 0.02780 0.01978 -0.1906 0.7802 0.0759
-4.750 0.3334 0.02700 0.01884 -0.1916 0.7742 0.0787
-4.500 0.3686 0.02567 0.01711 -0.1936 0.7702 0.0825
-4.250 0.3979 0.02485 0.01614 -0.1944 0.7647 0.0850
-4.000 0.4256 0.02440 0.01564 -0.1947 0.7584 0.0881
-3.750 0.4583 0.02364 0.01464 -0.1957 0.7538 0.0930
-3.500 0.4874 0.02304 0.01394 -0.1961 0.7477 0.0969
-3.250 0.5153 0.02263 0.01349 -0.1962 0.7408 0.1016
-3.000 0.5476 0.02204 0.01268 -0.1969 0.7362 0.1083
-2.750 0.5753 0.02168 0.01237 -0.1970 0.7302 0.1141
-2.500 0.6037 0.02139 0.01196 -0.1972 0.7240 0.1222
-2.250 0.6348 0.02094 0.01153 -0.1977 0.7195 0.1311
-2.000 0.6634 0.02071 0.01127 -0.1979 0.7139 0.1410
-1.750 0.6908 0.02058 0.01112 -0.1979 0.7075 0.1526
-1.500 0.7215 0.02029 0.01083 -0.1983 0.7024 0.1662
-1.250 0.7491 0.02021 0.01078 -0.1983 0.6959 0.1823
-1.000 0.7771 0.02013 0.01071 -0.1983 0.6890 0.2035
-0.750 0.8083 0.01991 0.01052 -0.1986 0.6838 0.2289
-0.500 0.8336 0.02002 0.01067 -0.1982 0.6757 0.2553
-0.250 0.8624 0.01997 0.01059 -0.1982 0.6693 0.2808
0.000 0.8907 0.01998 0.01058 -0.1981 0.6629 0.3040
0.250 0.9166 0.02009 0.01070 -0.1977 0.6550 0.3249
0.500 0.9467 0.02002 0.01056 -0.1978 0.6489 0.3445
0.750 0.9711 0.02021 0.01077 -0.1972 0.6398 0.3608
1.000 0.9996 0.02020 0.01071 -0.1970 0.6323 0.3794
1.250 1.0244 0.02038 0.01091 -0.1964 0.6231 0.3995
1.500 1.0517 0.02045 0.01094 -0.1961 0.6149 0.4226
1.750 1.0765 0.02063 0.01113 -0.1955 0.6057 0.4439
2.000 1.1029 0.02073 0.01121 -0.1951 0.5972 0.4645
2.250 1.1271 0.02091 0.01142 -0.1944 0.5875 0.4836
2.500 1.1531 0.02100 0.01147 -0.1939 0.5785 0.5026
2.750 1.1759 0.02123 0.01176 -0.1931 0.5678 0.5221
3.000 1.2020 0.02130 0.01180 -0.1926 0.5593 0.5456
3.500 1.2480 0.02173 0.01235 -0.1909 0.5404 0.6033
4.000 1.2930 0.02206 0.01283 -0.1890 0.5229 0.7002
4.250 1.3101 0.02200 0.01301 -0.1870 0.5146 1.0000
4.500 1.3343 0.02235 0.01323 -0.1864 0.5072 1.0000
4.750 1.3562 0.02277 0.01357 -0.1855 0.4985 1.0000
5.000 1.3788 0.02314 0.01384 -0.1846 0.4906 1.0000
5.250 1.3997 0.02360 0.01423 -0.1836 0.4823 1.0000
5.500 1.4226 0.02399 0.01450 -0.1828 0.4756 1.0000
5.750 1.4426 0.02453 0.01505 -0.1817 0.4687 1.0000
6.000 1.4655 0.02498 0.01542 -0.1809 0.4631 1.0000
6.250 1.4880 0.02547 0.01586 -0.1802 0.4579 1.0000
6.500 1.5075 0.02607 0.01649 -0.1791 0.4523 1.0000
6.750 1.5293 0.02658 0.01698 -0.1782 0.4471 1.0000
7.000 1.5545 0.02705 0.01735 -0.1779 0.4424 1.0000
7.250 1.5695 0.02775 0.01814 -0.1761 0.4370 1.0000
7.500 1.5883 0.02837 0.01881 -0.1748 0.4319 1.0000
7.750 1.6123 0.02889 0.01928 -0.1744 0.4275 1.0000
8.000 1.6335 0.02952 0.01993 -0.1735 0.4231 1.0000
8.250 1.6469 0.03033 0.02088 -0.1716 0.4181 1.0000
8.500 1.6646 0.03104 0.02163 -0.1703 0.4132 1.0000
8.750 1.6888 0.03157 0.02213 -0.1699 0.4086 1.0000
9.000 1.7029 0.03243 0.02308 -0.1682 0.4038 1.0000
9.250 1.7121 0.03343 0.02423 -0.1658 0.3985 1.0000
9.500 1.7285 0.03420 0.02507 -0.1645 0.3937 1.0000
9.750 1.7535 0.03473 0.02557 -0.1642 0.3895 1.0000
10.000 1.7580 0.03599 0.02702 -0.1614 0.3847 1.0000
10.250 1.7637 0.03724 0.02844 -0.1590 0.3794 1.0000
10.500 1.7776 0.03809 0.02935 -0.1574 0.3742 1.0000
10.750 1.7886 0.03909 0.03040 -0.1555 0.3688 1.0000
11.000 1.7832 0.04095 0.03248 -0.1522 0.3624 1.0000
11.250 1.7915 0.04203 0.03362 -0.1502 0.3562 1.0000
11.500 1.7928 0.04365 0.03536 -0.1477 0.3502 1.0000
11.750 1.7875 0.04580 0.03770 -0.1449 0.3436 1.0000
12.000 1.7966 0.04689 0.03883 -0.1432 0.3379 1.0000
12.250 1.7876 0.04959 0.04173 -0.1406 0.3316 1.0000
12.500 1.7843 0.05186 0.04414 -0.1384 0.3251 1.0000
12.750 1.7879 0.05355 0.04588 -0.1367 0.3193 1.0000
13.000 1.7726 0.05722 0.04979 -0.1344 0.3123 1.0000
13.250 1.7759 0.05901 0.05162 -0.1329 0.3061 1.0000
13.500 1.7597 0.06319 0.05601 -0.1312 0.2989 1.0000
13.750 1.7566 0.06593 0.05883 -0.1299 0.2920 1.0000
14.000 1.7449 0.06993 0.06297 -0.1288 0.2851 1.0000
14.250 1.7363 0.07365 0.06680 -0.1278 0.2779 1.0000
14.500 1.7280 0.07747 0.07071 -0.1271 0.2708 1.0000
14.750 1.7144 0.08213 0.07550 -0.1266 0.2636 1.0000
15.000 1.7113 0.08537 0.07880 -0.1260 0.2568 1.0000
15.250 1.6906 0.09139 0.08500 -0.1261 0.2502 1.0000
15.500 1.6980 0.09313 0.08672 -0.1255 0.2433 1.0000
15.750 1.6687 0.10078 0.09460 -0.1263 0.2371 1.0000
16.000 1.6730 0.10300 0.09680 -0.1260 0.2288 1.0000
16.250 1.6442 0.11095 0.10496 -0.1275 0.2223 1.0000
16.500 1.6444 0.11399 0.10800 -0.1277 0.2138 1.0000
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Polar data table (+)
Polar graphs
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