GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 100,000 Max Cl/Cd: 59.41 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe399-il-100000.txt Download as CSV file: xf-goe399-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3672 0.10817 0.10318 -0.0279 1.0000 0.0598
-8.500 -0.3743 0.10729 0.10241 -0.0300 1.0000 0.0601
-8.250 -0.3789 0.10578 0.10099 -0.0321 1.0000 0.0603
-8.000 -0.3784 0.10373 0.09899 -0.0357 1.0000 0.0604
-7.750 -0.3507 0.09379 0.08900 -0.0271 1.0000 0.0633
-7.500 -0.3472 0.09103 0.08630 -0.0262 1.0000 0.0661
-7.250 -0.3498 0.08887 0.08422 -0.0257 1.0000 0.0687
-7.000 -0.3512 0.08672 0.08215 -0.0271 1.0000 0.0713
-6.750 -0.3522 0.08527 0.08077 -0.0318 1.0000 0.0732
-6.500 -0.3481 0.08424 0.07969 -0.0394 1.0000 0.0740
-6.250 -0.3475 0.07915 0.07472 -0.0362 1.0000 0.0750
-6.000 -0.3462 0.07557 0.07123 -0.0312 1.0000 0.0766
-5.750 -0.3440 0.07300 0.06870 -0.0294 1.0000 0.0787
-5.500 -0.3414 0.07054 0.06627 -0.0290 1.0000 0.0815
-5.250 -0.3364 0.06814 0.06386 -0.0302 1.0000 0.0848
-5.000 -0.3195 0.06562 0.06108 -0.0378 1.0000 0.0887
-4.750 -0.3213 0.06218 0.05777 -0.0337 1.0000 0.0902
-4.500 -0.3177 0.05980 0.05543 -0.0316 1.0000 0.0929
-4.250 -0.2913 0.05780 0.05300 -0.0380 1.0000 0.1029
-4.000 -0.2919 0.05429 0.04973 -0.0342 1.0000 0.1056
-3.500 -0.2438 0.04828 0.04350 -0.0390 0.9953 0.1231
-3.250 -0.1977 0.04463 0.03961 -0.0454 0.9871 0.1404
-3.000 -0.1553 0.04137 0.03614 -0.0506 0.9791 0.1658
-2.750 -0.1120 0.03892 0.03340 -0.0556 0.9713 0.2049
-2.500 -0.0817 0.03622 0.03071 -0.0574 0.9633 0.2356
-2.000 0.0228 0.02988 0.02274 -0.0663 0.9497 0.1612
-1.750 0.0705 0.02596 0.01800 -0.0683 0.9442 0.1123
-1.500 0.1094 0.02447 0.01609 -0.0701 0.9365 0.1135
-1.250 0.1516 0.02290 0.01417 -0.0723 0.9295 0.1115
-1.000 0.1894 0.02179 0.01280 -0.0738 0.9209 0.1128
-0.750 0.2339 0.02068 0.01156 -0.0766 0.9145 0.1205
-0.500 0.2702 0.01995 0.01078 -0.0779 0.9050 0.1298
-0.250 0.3173 0.01884 0.00977 -0.0811 0.8994 0.1448
0.000 0.3505 0.01812 0.00919 -0.0818 0.8888 0.1754
0.250 0.4253 0.01514 0.00816 -0.0906 0.8865 1.0000
0.500 0.4591 0.01510 0.00790 -0.0913 0.8747 1.0000
0.750 0.4929 0.01502 0.00768 -0.0919 0.8631 1.0000
1.000 0.5262 0.01491 0.00746 -0.0923 0.8512 1.0000
1.250 0.5580 0.01482 0.00727 -0.0923 0.8389 1.0000
1.500 0.5874 0.01476 0.00714 -0.0919 0.8251 1.0000
1.750 0.6147 0.01475 0.00707 -0.0911 0.8100 1.0000
2.000 0.6409 0.01478 0.00703 -0.0900 0.7938 1.0000
2.250 0.6668 0.01480 0.00699 -0.0889 0.7765 1.0000
2.500 0.6928 0.01483 0.00697 -0.0877 0.7590 1.0000
2.750 0.7188 0.01490 0.00697 -0.0866 0.7420 1.0000
3.000 0.7430 0.01508 0.00711 -0.0853 0.7235 1.0000
3.250 0.7673 0.01529 0.00730 -0.0842 0.7055 1.0000
3.500 0.7922 0.01552 0.00753 -0.0832 0.6885 1.0000
3.750 0.8172 0.01575 0.00775 -0.0823 0.6722 1.0000
4.000 0.8422 0.01600 0.00800 -0.0813 0.6564 1.0000
4.250 0.8672 0.01622 0.00820 -0.0804 0.6401 1.0000
4.500 0.8901 0.01643 0.00850 -0.0791 0.6204 1.0000
4.750 0.9140 0.01653 0.00860 -0.0778 0.6007 1.0000
5.000 0.9381 0.01669 0.00874 -0.0766 0.5822 1.0000
5.250 0.9616 0.01697 0.00911 -0.0755 0.5645 1.0000
5.500 0.9847 0.01713 0.00934 -0.0742 0.5439 1.0000
5.750 1.0063 0.01725 0.00947 -0.0725 0.5187 1.0000
6.000 1.0284 0.01746 0.00970 -0.0710 0.4958 1.0000
6.250 1.0499 0.01775 0.01007 -0.0696 0.4725 1.0000
6.500 1.0693 0.01800 0.01035 -0.0676 0.4420 1.0000
6.750 1.0834 0.01825 0.01062 -0.0647 0.3898 1.0000
7.000 1.0875 0.01922 0.01099 -0.0605 0.2525 1.0000
7.250 1.0844 0.02220 0.01274 -0.0564 0.1247 1.0000
7.500 1.0893 0.02441 0.01478 -0.0531 0.0984 1.0000
7.750 1.0955 0.02649 0.01677 -0.0498 0.0835 1.0000
8.000 1.1068 0.02838 0.01860 -0.0473 0.0723 1.0000
8.250 1.1256 0.03074 0.02089 -0.0458 0.0649 1.0000
8.500 1.1506 0.03303 0.02321 -0.0451 0.0595 1.0000
8.750 1.1774 0.03615 0.02640 -0.0450 0.0544 1.0000
9.000 1.2007 0.03867 0.02924 -0.0439 0.0518 1.0000
9.250 1.2216 0.04169 0.03262 -0.0426 0.0506 1.0000
9.500 1.2378 0.04504 0.03639 -0.0408 0.0502 1.0000
9.750 1.2489 0.04831 0.04007 -0.0387 0.0495 1.0000
10.000 1.2567 0.05149 0.04361 -0.0365 0.0484 1.0000
10.250 1.2633 0.05476 0.04719 -0.0345 0.0472 1.0000
10.500 1.2577 0.05864 0.05159 -0.0312 0.0482 1.0000
10.750 1.2464 0.06288 0.05630 -0.0278 0.0500 1.0000
11.000 1.2332 0.06691 0.06066 -0.0246 0.0516 1.0000
11.250 1.2175 0.07087 0.06484 -0.0218 0.0528 1.0000
11.500 1.2019 0.07529 0.06945 -0.0200 0.0540 1.0000
11.750 1.0789 0.07310 0.06774 -0.0135 0.0526 1.0000
12.000 1.0528 0.07879 0.07360 -0.0141 0.0532 1.0000
12.250 1.0267 0.08499 0.07996 -0.0156 0.0539 1.0000
12.500 1.0020 0.09161 0.08671 -0.0177 0.0547 1.0000
12.750 0.9858 0.09847 0.09364 -0.0196 0.0558 1.0000
13.000 0.8769 0.11713 0.11270 -0.0359 0.0642 1.0000
13.250 0.8560 0.12446 0.12005 -0.0396 0.0670 1.0000
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