GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 50,000 Max Cl/Cd: 20.19 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe431-il-50000.txt Download as CSV file: xf-goe431-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3577 0.12844 0.12260 -0.0130 1.0000 0.1818
-7.250 -0.3752 0.12852 0.12277 -0.0120 1.0000 0.1837
-7.000 -0.3981 0.12904 0.12339 -0.0105 1.0000 0.1844
-6.750 -0.3859 0.12358 0.11795 -0.0095 1.0000 0.1865
-6.500 -0.3767 0.11973 0.11409 -0.0080 1.0000 0.1899
-6.250 -0.3809 0.11765 0.11206 -0.0063 1.0000 0.1930
-6.000 -0.3915 0.11622 0.11069 -0.0046 1.0000 0.1960
-5.750 -0.4061 0.11535 0.10989 -0.0045 1.0000 0.1990
-5.500 -0.4187 0.11467 0.10928 -0.0087 1.0000 0.2006
-5.250 -0.4078 0.10931 0.10394 -0.0038 1.0000 0.2039
-5.000 -0.4037 0.10656 0.10121 -0.0024 1.0000 0.2103
-4.750 -0.4060 0.10533 0.10000 -0.0112 1.0000 0.2166
-4.500 -0.4012 0.10084 0.09555 -0.0051 1.0000 0.2203
-4.250 -0.3950 0.09798 0.09269 -0.0049 1.0000 0.2275
-4.000 -0.3842 0.09457 0.08928 -0.0116 1.0000 0.2343
-3.750 -0.3775 0.09174 0.08645 -0.0089 1.0000 0.2450
-3.500 -0.3671 0.08833 0.08305 -0.0101 1.0000 0.2551
-3.250 -0.3504 0.08486 0.07955 -0.0142 1.0000 0.2688
-3.000 -0.3364 0.08175 0.07642 -0.0152 1.0000 0.2859
-2.750 -0.3220 0.07879 0.07344 -0.0159 1.0000 0.3062
-2.500 -0.3026 0.07568 0.07028 -0.0185 1.0000 0.3331
-2.000 -0.2662 0.07091 0.06539 -0.0205 1.0000 0.4097
-1.250 -0.1153 0.05784 0.05139 -0.0526 1.0000 0.4262
-1.000 -0.0956 0.05597 0.04945 -0.0529 1.0000 0.4364
-0.750 -0.0520 0.05435 0.04755 -0.0606 1.0000 0.4368
-0.500 0.0005 0.05299 0.04580 -0.0712 1.0000 0.4230
-0.250 0.0333 0.05236 0.04499 -0.0760 1.0000 0.4187
0.000 0.1453 0.05275 0.04471 -0.0964 0.9732 0.4051
0.250 0.2344 0.05277 0.04429 -0.1099 0.9398 0.4023
0.500 0.3076 0.05249 0.04362 -0.1200 0.9152 0.3985
0.750 0.3623 0.05222 0.04312 -0.1261 0.8899 0.3992
1.000 0.4236 0.05207 0.04275 -0.1324 0.8693 0.4050
1.250 0.4713 0.05178 0.04223 -0.1367 0.8443 0.4095
1.500 0.5255 0.05133 0.04168 -0.1410 0.8243 0.4144
1.750 0.5821 0.05074 0.04094 -0.1455 0.8060 0.4225
2.000 0.6165 0.05051 0.04062 -0.1468 0.7806 0.4301
2.250 0.6627 0.04996 0.03999 -0.1491 0.7626 0.4451
2.500 0.7058 0.04936 0.03937 -0.1508 0.7459 0.4635
2.750 0.7466 0.04872 0.03872 -0.1522 0.7299 0.4859
3.000 0.7835 0.04816 0.03817 -0.1530 0.7145 0.5145
3.250 0.8163 0.04771 0.03778 -0.1533 0.6997 0.5589
3.500 0.8436 0.04732 0.03764 -0.1530 0.6856 0.6334
3.750 0.8592 0.04663 0.03762 -0.1513 0.6721 1.0000
4.000 0.8884 0.04759 0.03818 -0.1525 0.6595 1.0000
4.250 0.9382 0.04646 0.03685 -0.1543 0.6540 1.0000
4.500 0.9492 0.04828 0.03859 -0.1531 0.6410 1.0000
4.750 0.9579 0.05051 0.04076 -0.1520 0.6295 1.0000
5.000 0.9989 0.04993 0.04011 -0.1528 0.6248 1.0000
5.250 0.9876 0.05440 0.04458 -0.1511 0.6134 1.0000
5.500 1.0283 0.05384 0.04402 -0.1517 0.6094 1.0000
5.750 1.0013 0.06007 0.05027 -0.1496 0.5983 1.0000
6.000 1.0399 0.05979 0.04999 -0.1501 0.5944 1.0000
6.250 0.9902 0.06878 0.05902 -0.1481 0.5864 1.0000
6.500 0.9933 0.07243 0.06270 -0.1478 0.5824 1.0000
6.750 1.0269 0.07300 0.06330 -0.1482 0.5788 1.0000
7.000 0.9901 0.08073 0.07108 -0.1472 0.5756 1.0000
7.250 0.9761 0.08628 0.07668 -0.1470 0.5749 1.0000
7.500 0.9667 0.09124 0.08170 -0.1470 0.5740 1.0000
7.750 0.9606 0.09586 0.08638 -0.1470 0.5735 1.0000
8.000 0.9576 0.09995 0.09055 -0.1469 0.5711 1.0000
8.250 0.9864 0.10106 0.09172 -0.1467 0.5610 1.0000
8.500 0.9754 0.10574 0.09646 -0.1466 0.5580 1.0000
8.750 0.9740 0.10973 0.10054 -0.1466 0.5550 1.0000
9.000 0.9954 0.11168 0.10257 -0.1464 0.5447 1.0000
9.250 0.9879 0.11640 0.10738 -0.1468 0.5435 1.0000
9.500 0.9843 0.12109 0.11217 -0.1474 0.5440 1.0000
9.750 0.9874 0.12585 0.11706 -0.1485 0.5461 1.0000
10.000 1.0231 0.12564 0.11696 -0.1470 0.5179 1.0000
10.250 1.0231 0.13067 0.12209 -0.1480 0.5172 1.0000
10.500 0.9552 0.14513 0.13664 -0.1548 0.5937 1.0000
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Polar data table (+)
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