GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 100,000 Max Cl/Cd: 45.62 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe441-il-100000.txt Download as CSV file: xf-goe441-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 0.0837 0.10209 0.09731 -0.0984 0.9168 0.1151
-7.750 0.0739 0.10206 0.09730 -0.1052 0.9055 0.1188
-7.500 0.0730 0.09950 0.09478 -0.1058 0.8931 0.1197
-7.250 0.1258 0.09271 0.08793 -0.1076 0.8918 0.1221
-7.000 0.1570 0.08871 0.08390 -0.1111 0.8872 0.1257
-6.750 0.1609 0.08685 0.08205 -0.1111 0.8737 0.1294
-6.500 0.1336 0.08781 0.08306 -0.1207 0.8541 0.1335
-6.250 0.1717 0.08164 0.07684 -0.1160 0.8517 0.1353
-6.000 0.1905 0.07893 0.07413 -0.1138 0.8397 0.1386
-5.750 0.2085 0.07633 0.07147 -0.1187 0.8308 0.1466
-5.500 0.2156 0.07338 0.06851 -0.1234 0.8156 0.1503
-5.250 0.2325 0.07078 0.06589 -0.1202 0.8021 0.1528
-5.000 0.2529 0.06822 0.06325 -0.1213 0.7899 0.1584
-4.750 0.2755 0.06458 0.05950 -0.1308 0.7773 0.1669
-4.500 0.2896 0.06259 0.05748 -0.1277 0.7619 0.1700
-4.250 0.3193 0.05926 0.05400 -0.1395 0.7467 0.1834
-4.000 0.3353 0.05731 0.05198 -0.1349 0.7358 0.1867
-3.750 0.4340 0.03650 0.02985 -0.1795 0.7251 0.1207
-3.500 0.4815 0.03202 0.02449 -0.1869 0.7132 0.1191
-3.250 0.5114 0.03067 0.02316 -0.1876 0.7028 0.1236
-3.000 0.5440 0.02893 0.02105 -0.1897 0.6902 0.1272
-2.750 0.5861 0.02687 0.01825 -0.1931 0.6817 0.1343
-2.500 0.6115 0.02640 0.01785 -0.1929 0.6706 0.1415
-2.250 0.6470 0.02536 0.01641 -0.1945 0.6629 0.1520
-2.000 0.6750 0.02508 0.01596 -0.1947 0.6529 0.1639
-1.750 0.7081 0.02452 0.01527 -0.1955 0.6464 0.1778
-1.500 0.7336 0.02434 0.01510 -0.1954 0.6371 0.1911
-1.250 0.7655 0.02394 0.01454 -0.1961 0.6307 0.2068
-1.000 0.7940 0.02379 0.01430 -0.1963 0.6239 0.2221
-0.750 0.8226 0.02368 0.01409 -0.1965 0.6170 0.2382
-0.500 0.8549 0.02337 0.01367 -0.1972 0.6116 0.2566
-0.250 0.8798 0.02338 0.01381 -0.1969 0.6047 0.2750
0.000 0.9084 0.02326 0.01378 -0.1971 0.5988 0.3006
0.250 0.9407 0.02311 0.01372 -0.1978 0.5943 0.3457
0.500 0.9662 0.02339 0.01426 -0.1975 0.5885 0.4152
0.750 0.9923 0.02364 0.01469 -0.1971 0.5828 0.4950
1.000 1.0208 0.02372 0.01482 -0.1969 0.5781 0.5665
1.250 1.0466 0.02400 0.01516 -0.1962 0.5735 0.6254
1.500 1.0666 0.02446 0.01580 -0.1948 0.5683 0.6744
1.750 1.0897 0.02472 0.01613 -0.1938 0.5635 0.7306
2.000 1.1135 0.02464 0.01612 -0.1925 0.5595 0.8088
2.250 1.1350 0.02488 0.01643 -0.1914 0.5551 1.0000
2.500 1.1592 0.02574 0.01723 -0.1915 0.5498 1.0000
2.750 1.1872 0.02637 0.01773 -0.1919 0.5451 1.0000
3.000 1.2191 0.02687 0.01800 -0.1927 0.5411 1.0000
3.250 1.2445 0.02771 0.01876 -0.1927 0.5368 1.0000
3.500 1.2626 0.02873 0.01984 -0.1917 0.5316 1.0000
3.750 1.2865 0.02951 0.02057 -0.1913 0.5270 1.0000
4.000 1.3161 0.03007 0.02099 -0.1917 0.5230 1.0000
4.250 1.3448 0.03088 0.02166 -0.1921 0.5192 1.0000
4.500 1.3533 0.03232 0.02329 -0.1897 0.5139 1.0000
4.750 1.3728 0.03332 0.02432 -0.1888 0.5092 1.0000
5.000 1.3999 0.03395 0.02487 -0.1889 0.5050 1.0000
5.250 1.4332 0.03452 0.02527 -0.1898 0.5015 1.0000
5.500 1.4346 0.03644 0.02742 -0.1866 0.4964 1.0000
5.750 1.4412 0.03810 0.02921 -0.1841 0.4912 1.0000
6.000 1.4657 0.03882 0.02990 -0.1838 0.4870 1.0000
6.250 1.4994 0.03918 0.03015 -0.1846 0.4835 1.0000
6.500 1.5098 0.04092 0.03198 -0.1827 0.4794 1.0000
6.750 1.4723 0.04498 0.03640 -0.1752 0.4727 1.0000
7.000 1.4880 0.04615 0.03759 -0.1739 0.4684 1.0000
7.250 1.5316 0.04579 0.03711 -0.1757 0.4653 1.0000
7.500 1.5804 0.04552 0.03669 -0.1783 0.4625 1.0000
7.750 1.3088 0.06837 0.06040 -0.1541 0.4448 1.0000
8.000 1.3757 0.06427 0.05620 -0.1550 0.4448 1.0000
8.250 1.4500 0.06030 0.05212 -0.1572 0.4445 1.0000
8.500 1.5369 0.05649 0.04817 -0.1618 0.4437 1.0000
8.750 0.9692 0.13173 0.12455 -0.1587 0.4118 1.0000
9.000 0.9899 0.13361 0.12640 -0.1584 0.4099 1.0000
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