GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 100,000 Max Cl/Cd: 55.72 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe199-il-100000.txt Download as CSV file: xf-goe199-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 199 (L.F.G. 5406) 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3170 0.09111 0.08660 -0.0284 1.0000 0.0502
-6.750 -0.3134 0.08792 0.08347 -0.0267 1.0000 0.0514
-6.500 -0.3116 0.08548 0.08108 -0.0260 1.0000 0.0528
-6.250 -0.3119 0.08343 0.07909 -0.0253 1.0000 0.0545
-6.000 -0.3125 0.08158 0.07727 -0.0250 1.0000 0.0564
-5.750 -0.3075 0.08014 0.07582 -0.0271 1.0000 0.0589
-5.500 -0.2796 0.08096 0.07632 -0.0375 1.0000 0.0604
-5.250 -0.2858 0.07554 0.07111 -0.0330 1.0000 0.0612
-5.000 -0.2866 0.07217 0.06783 -0.0298 1.0000 0.0623
-4.750 -0.2813 0.06951 0.06519 -0.0286 1.0000 0.0640
-4.500 -0.2701 0.06701 0.06267 -0.0291 1.0000 0.0666
-4.250 -0.2485 0.06480 0.06034 -0.0324 1.0000 0.0711
-4.000 -0.2171 0.06198 0.05729 -0.0379 0.9995 0.0742
-3.750 -0.1910 0.05770 0.05305 -0.0402 0.9948 0.0788
-3.500 -0.1356 0.05434 0.04934 -0.0494 0.9888 0.0880
-3.250 -0.1010 0.05063 0.04563 -0.0532 0.9838 0.0943
-3.000 -0.0565 0.04752 0.04227 -0.0591 0.9772 0.1042
-2.750 -0.0101 0.04467 0.03920 -0.0648 0.9716 0.1185
-2.500 0.0275 0.04205 0.03648 -0.0686 0.9647 0.1350
-2.250 0.0699 0.03961 0.03390 -0.0730 0.9584 0.1553
-2.000 0.1114 0.03719 0.03134 -0.0772 0.9520 0.1819
-1.750 0.1510 0.03507 0.02910 -0.0808 0.9444 0.2239
-1.500 0.1933 0.03235 0.02646 -0.0848 0.9401 0.2900
-1.000 0.2725 0.02713 0.02142 -0.0895 0.9251 0.4416
-0.750 0.3181 0.02517 0.01932 -0.0924 0.9129 0.4695
-0.500 0.4010 0.02504 0.01778 -0.1002 0.9005 0.2457
-0.250 0.4521 0.02383 0.01573 -0.1007 0.8891 0.1405
0.000 0.4898 0.02256 0.01416 -0.1006 0.8773 0.1254
0.250 0.5221 0.02167 0.01297 -0.0997 0.8640 0.1134
0.500 0.5499 0.02070 0.01192 -0.0984 0.8494 0.1076
0.750 0.5771 0.02006 0.01111 -0.0969 0.8344 0.1029
1.000 0.6034 0.01959 0.01054 -0.0953 0.8189 0.1009
1.250 0.6289 0.01896 0.00988 -0.0937 0.8030 0.1006
1.500 0.6534 0.01829 0.00922 -0.0920 0.7869 0.1033
1.750 0.6786 0.01791 0.00882 -0.0907 0.7682 0.1093
2.000 0.7042 0.01762 0.00844 -0.0894 0.7490 0.1138
2.250 0.7302 0.01733 0.00807 -0.0882 0.7296 0.1219
2.500 0.7565 0.01703 0.00776 -0.0869 0.7099 0.1504
2.750 0.7832 0.01533 0.00752 -0.0861 0.6855 1.0000
3.000 0.8085 0.01535 0.00727 -0.0848 0.6595 1.0000
3.250 0.8334 0.01541 0.00711 -0.0836 0.6294 1.0000
3.500 0.8580 0.01554 0.00700 -0.0824 0.5950 1.0000
3.750 0.8820 0.01583 0.00697 -0.0812 0.5580 1.0000
4.000 0.9057 0.01633 0.00718 -0.0801 0.5183 1.0000
4.250 0.9293 0.01697 0.00749 -0.0791 0.4816 1.0000
4.500 0.9533 0.01762 0.00790 -0.0784 0.4491 1.0000
4.750 0.9778 0.01827 0.00833 -0.0778 0.4240 1.0000
5.000 1.0028 0.01893 0.00886 -0.0774 0.4042 1.0000
5.250 1.0281 0.01959 0.00941 -0.0770 0.3886 1.0000
5.500 1.0537 0.02028 0.00997 -0.0767 0.3763 1.0000
5.750 1.0795 0.02094 0.01063 -0.0765 0.3654 1.0000
6.000 1.1055 0.02167 0.01139 -0.0763 0.3568 1.0000
6.250 1.1319 0.02241 0.01211 -0.0762 0.3499 1.0000
6.500 1.1582 0.02322 0.01298 -0.0761 0.3442 1.0000
6.750 1.1842 0.02401 0.01390 -0.0760 0.3388 1.0000
7.000 1.2109 0.02485 0.01480 -0.0760 0.3346 1.0000
7.250 1.2365 0.02572 0.01579 -0.0758 0.3296 1.0000
7.500 1.2605 0.02632 0.01653 -0.0754 0.3211 1.0000
7.750 1.2833 0.02685 0.01719 -0.0748 0.3106 1.0000
8.000 1.3071 0.02736 0.01766 -0.0743 0.3007 1.0000
8.250 1.3289 0.02777 0.01828 -0.0735 0.2906 1.0000
8.500 1.3492 0.02807 0.01873 -0.0725 0.2780 1.0000
8.750 1.3684 0.02827 0.01909 -0.0713 0.2644 1.0000
9.000 1.3850 0.02827 0.01924 -0.0697 0.2479 1.0000
9.250 1.3968 0.02811 0.01924 -0.0673 0.2257 1.0000
9.500 1.4031 0.02795 0.01936 -0.0640 0.1758 1.0000
9.750 1.3993 0.03052 0.02107 -0.0604 0.0876 1.0000
10.000 1.3977 0.03307 0.02362 -0.0567 0.0761 1.0000
10.250 1.3903 0.03554 0.02614 -0.0525 0.0705 1.0000
10.500 1.3892 0.03749 0.02832 -0.0490 0.0658 1.0000
10.750 1.3847 0.03983 0.03079 -0.0459 0.0626 1.0000
11.000 1.3778 0.04256 0.03360 -0.0431 0.0604 1.0000
11.250 1.3740 0.04533 0.03640 -0.0407 0.0586 1.0000
11.500 1.3780 0.04758 0.03881 -0.0388 0.0566 1.0000
11.750 1.3826 0.04989 0.04124 -0.0371 0.0542 1.0000
12.000 1.3881 0.05224 0.04362 -0.0356 0.0516 1.0000
12.250 1.4230 0.05441 0.04549 -0.0341 0.0484 1.0000
12.500 1.4385 0.05682 0.04815 -0.0328 0.0477 1.0000
12.750 1.4506 0.05963 0.05123 -0.0315 0.0470 1.0000
13.000 1.4546 0.06269 0.05458 -0.0300 0.0463 1.0000
13.250 1.4529 0.06598 0.05816 -0.0286 0.0455 1.0000
13.500 1.4476 0.06953 0.06200 -0.0274 0.0449 1.0000
13.750 1.4391 0.07344 0.06618 -0.0266 0.0444 1.0000
14.000 1.4273 0.07776 0.07079 -0.0261 0.0442 1.0000
14.250 1.4123 0.08258 0.07589 -0.0263 0.0443 1.0000
14.500 1.3946 0.08789 0.08148 -0.0271 0.0445 1.0000
14.750 1.3749 0.09371 0.08756 -0.0287 0.0448 1.0000
15.000 1.3535 0.10008 0.09419 -0.0312 0.0451 1.0000
15.250 1.3309 0.10704 0.10138 -0.0345 0.0454 1.0000
15.500 1.3075 0.11470 0.10926 -0.0388 0.0458 1.0000
15.750 1.2835 0.12314 0.11789 -0.0439 0.0463 1.0000
16.000 1.2593 0.13239 0.12731 -0.0500 0.0468 1.0000
16.250 1.2363 0.14220 0.13726 -0.0564 0.0475 1.0000
16.500 1.2168 0.15194 0.14708 -0.0624 0.0481 1.0000
16.750 1.1321 0.18780 0.18300 -0.0870 0.0586 1.0000
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Polar data table (+)
Polar graphs
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