GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 100,000 Max Cl/Cd: 41.38 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe518-il-100000.txt Download as CSV file: xf-goe518-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0873 0.11095 0.10663 -0.0712 0.9189 0.1079
-8.250 -0.1181 0.10896 0.10467 -0.0804 0.9088 0.1107
-8.000 -0.1594 0.10741 0.10307 -0.0828 0.8929 0.1111
-7.750 -0.0536 0.09975 0.09544 -0.0804 0.8949 0.1162
-7.500 -0.0520 0.09711 0.09283 -0.0810 0.8834 0.1196
-7.250 -0.0730 0.09459 0.09030 -0.0840 0.8723 0.1234
-7.000 -0.1260 0.09351 0.08908 -0.0849 0.8524 0.1250
-6.750 -0.0877 0.08783 0.08353 -0.0846 0.8484 0.1275
-6.500 -0.0523 0.08403 0.07972 -0.0860 0.8445 0.1319
-6.250 -0.0575 0.08163 0.07730 -0.0849 0.8314 0.1357
-6.000 -0.0977 0.07986 0.07515 -0.0854 0.8148 0.1416
-5.750 -0.0568 0.07451 0.07001 -0.0862 0.8116 0.1444
-5.500 -0.0239 0.07075 0.06621 -0.0882 0.8083 0.1509
-5.250 -0.0462 0.06909 0.06420 -0.0861 0.7929 0.1595
-5.000 -0.0064 0.06444 0.05969 -0.0876 0.7907 0.1639
-4.750 -0.0049 0.06285 0.05806 -0.0844 0.7774 0.1699
-4.500 0.0199 0.05894 0.05400 -0.0858 0.7736 0.1826
-4.250 0.0147 0.05804 0.05281 -0.0824 0.7597 0.1971
-4.000 0.0521 0.05465 0.04942 -0.0838 0.7566 0.2127
-3.750 0.0608 0.05181 0.04662 -0.0811 0.7458 0.2212
-3.500 0.0902 0.04887 0.04359 -0.0815 0.7402 0.2419
-2.500 0.2102 0.03495 0.02710 -0.0804 0.7073 0.1223
-2.250 0.2691 0.03148 0.02288 -0.0839 0.7022 0.1092
-2.000 0.2926 0.02994 0.02113 -0.0824 0.6888 0.1070
-1.750 0.3404 0.02800 0.01881 -0.0849 0.6779 0.1051
-1.500 0.4010 0.02628 0.01669 -0.0900 0.6661 0.1062
-1.250 0.4309 0.02559 0.01575 -0.0897 0.6508 0.1088
-1.000 0.4644 0.02497 0.01486 -0.0901 0.6357 0.1107
-0.750 0.5016 0.02409 0.01390 -0.0914 0.6208 0.1137
-0.500 0.5393 0.02353 0.01324 -0.0929 0.6065 0.1188
-0.250 0.5733 0.02310 0.01269 -0.0937 0.5929 0.1276
0.000 0.5882 0.02299 0.01260 -0.0911 0.5795 0.1373
0.250 0.6146 0.02270 0.01226 -0.0905 0.5680 0.1550
0.500 0.8702 0.02159 0.01272 -0.1352 0.5406 1.0000
0.750 0.8897 0.02195 0.01287 -0.1337 0.5319 1.0000
1.000 0.9055 0.02230 0.01308 -0.1315 0.5229 1.0000
1.250 0.9299 0.02264 0.01319 -0.1310 0.5157 1.0000
1.500 0.9398 0.02308 0.01359 -0.1278 0.5080 1.0000
1.750 0.9651 0.02341 0.01371 -0.1274 0.5017 1.0000
2.000 0.9822 0.02389 0.01411 -0.1256 0.4957 1.0000
2.250 0.9943 0.02438 0.01457 -0.1228 0.4898 1.0000
2.500 1.0184 0.02477 0.01480 -0.1223 0.4846 1.0000
2.750 1.0453 0.02526 0.01512 -0.1224 0.4800 1.0000
3.000 1.0500 0.02587 0.01581 -0.1183 0.4749 1.0000
3.250 1.0648 0.02637 0.01627 -0.1161 0.4701 1.0000
3.500 1.0914 0.02680 0.01655 -0.1161 0.4657 1.0000
3.750 1.1169 0.02739 0.01701 -0.1160 0.4619 1.0000
4.000 1.1189 0.02813 0.01787 -0.1115 0.4581 1.0000
4.250 1.1280 0.02883 0.01861 -0.1084 0.4543 1.0000
4.500 1.1444 0.02946 0.01921 -0.1066 0.4509 1.0000
4.750 1.1696 0.03003 0.01968 -0.1065 0.4478 1.0000
5.000 1.2043 0.03072 0.02022 -0.1082 0.4449 1.0000
5.250 1.1956 0.03173 0.02142 -0.1020 0.4421 1.0000
5.500 1.1921 0.03275 0.02255 -0.0969 0.4391 1.0000
5.750 1.1950 0.03369 0.02355 -0.0929 0.4358 1.0000
6.000 1.2067 0.03449 0.02435 -0.0905 0.4328 1.0000
6.250 1.2276 0.03522 0.02505 -0.0898 0.4302 1.0000
6.500 1.2580 0.03597 0.02572 -0.0908 0.4279 1.0000
6.750 1.2559 0.03736 0.02720 -0.0863 0.4258 1.0000
7.000 1.2122 0.03930 0.02936 -0.0749 0.4237 1.0000
7.250 1.1483 0.04244 0.03277 -0.0619 0.4213 1.0000
7.500 0.4594 0.11496 0.10703 -0.0405 0.4700 1.0000
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Polar data table (+)
Polar graphs
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