GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 50,000 Max Cl/Cd: 41.89 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe400-il-50000-n5.txt Download as CSV file: xf-goe400-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 400 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3714 0.10724 0.10051 -0.0076 1.0000 0.0926
-7.750 -0.3698 0.10572 0.09909 -0.0110 1.0000 0.0938
-7.500 -0.3634 0.10386 0.09728 -0.0163 1.0000 0.0943
-7.250 -0.3530 0.09925 0.09273 -0.0167 1.0000 0.0952
-7.000 -0.3410 0.09451 0.08801 -0.0141 1.0000 0.0989
-6.750 -0.3308 0.09161 0.08515 -0.0163 1.0000 0.1029
-6.500 -0.3187 0.08956 0.08314 -0.0226 1.0000 0.1062
-6.250 -0.3025 0.08730 0.08087 -0.0297 1.0000 0.1071
-6.000 -0.2884 0.08365 0.07724 -0.0325 1.0000 0.1076
-5.750 -0.2797 0.07925 0.07291 -0.0304 1.0000 0.1088
-5.500 -0.2697 0.07590 0.06961 -0.0293 1.0000 0.1119
-5.250 -0.2554 0.07338 0.06711 -0.0320 1.0000 0.1182
-4.750 -0.2242 0.06794 0.06166 -0.0389 1.0000 0.1223
-4.500 -0.2166 0.06513 0.05890 -0.0381 1.0000 0.1233
-4.250 -0.2082 0.06274 0.05652 -0.0382 1.0000 0.1241
-4.000 -0.1628 0.05694 0.05038 -0.0470 0.9905 0.0915
-3.750 -0.1163 0.05277 0.04596 -0.0549 0.9778 0.0915
-3.500 -0.0706 0.04877 0.04171 -0.0618 0.9655 0.0897
-3.000 0.0286 0.04026 0.03227 -0.0761 0.9417 0.0821
-2.750 0.0714 0.03719 0.02883 -0.0806 0.9294 0.0819
-2.500 0.1137 0.03439 0.02561 -0.0845 0.9172 0.0834
-2.250 0.1492 0.03306 0.02416 -0.0867 0.9038 0.0884
-2.000 0.1869 0.03099 0.02164 -0.0890 0.8900 0.0914
-1.750 0.2234 0.02896 0.01911 -0.0908 0.8765 0.0930
-1.500 0.2576 0.02729 0.01701 -0.0919 0.8630 0.0955
-1.250 0.2890 0.02620 0.01571 -0.0924 0.8494 0.0992
-1.000 0.3210 0.02504 0.01410 -0.0928 0.8362 0.1057
-0.750 0.3500 0.02439 0.01332 -0.0928 0.8229 0.1175
-0.500 0.3791 0.02369 0.01238 -0.0925 0.8101 0.1316
-0.250 0.4094 0.02310 0.01148 -0.0923 0.7979 0.1507
0.000 0.4371 0.02274 0.01111 -0.0920 0.7852 0.1727
0.250 0.4645 0.02250 0.01072 -0.0915 0.7722 0.1945
0.500 0.4915 0.02222 0.01036 -0.0909 0.7595 0.2073
0.750 0.5181 0.02202 0.01010 -0.0902 0.7473 0.2188
1.000 0.5445 0.02187 0.00988 -0.0895 0.7355 0.2285
1.250 0.5709 0.02177 0.00971 -0.0887 0.7242 0.2368
1.500 0.5965 0.02174 0.00971 -0.0880 0.7115 0.2463
1.750 0.6221 0.02173 0.00978 -0.0874 0.6994 0.2618
2.000 0.6482 0.02167 0.00986 -0.0868 0.6878 0.2901
2.250 0.6747 0.02035 0.00987 -0.0862 0.6771 1.0000
2.500 0.7009 0.02070 0.01001 -0.0855 0.6649 1.0000
2.750 0.7266 0.02107 0.01027 -0.0849 0.6525 1.0000
3.000 0.7523 0.02143 0.01053 -0.0842 0.6406 1.0000
3.250 0.7781 0.02177 0.01079 -0.0834 0.6293 1.0000
3.500 0.8038 0.02210 0.01107 -0.0827 0.6180 1.0000
3.750 0.8288 0.02252 0.01150 -0.0820 0.6053 1.0000
4.000 0.8537 0.02293 0.01194 -0.0813 0.5928 1.0000
4.250 0.8787 0.02333 0.01239 -0.0806 0.5806 1.0000
4.500 0.9039 0.02370 0.01278 -0.0798 0.5688 1.0000
4.750 0.9292 0.02402 0.01312 -0.0789 0.5572 1.0000
5.000 0.9535 0.02447 0.01367 -0.0782 0.5437 1.0000
5.250 0.9777 0.02491 0.01424 -0.0774 0.5302 1.0000
5.500 1.0017 0.02530 0.01473 -0.0765 0.5160 1.0000
5.750 1.0256 0.02563 0.01516 -0.0755 0.5010 1.0000
6.000 1.0492 0.02594 0.01559 -0.0744 0.4852 1.0000
6.250 1.0727 0.02621 0.01596 -0.0732 0.4688 1.0000
6.500 1.0953 0.02653 0.01638 -0.0720 0.4505 1.0000
6.750 1.1170 0.02691 0.01691 -0.0708 0.4301 1.0000
7.000 1.1389 0.02720 0.01731 -0.0694 0.4095 1.0000
7.250 1.1598 0.02769 0.01795 -0.0682 0.3884 1.0000
7.500 1.1806 0.02826 0.01868 -0.0670 0.3682 1.0000
7.750 1.2012 0.02885 0.01940 -0.0657 0.3488 1.0000
8.000 1.2203 0.02966 0.02043 -0.0644 0.3267 1.0000
8.250 1.2385 0.03046 0.02137 -0.0629 0.3035 1.0000
8.500 1.2532 0.03147 0.02247 -0.0613 0.2734 1.0000
8.750 1.2615 0.03276 0.02363 -0.0594 0.2311 1.0000
9.000 1.2654 0.03460 0.02522 -0.0576 0.1848 1.0000
9.250 1.2683 0.03680 0.02722 -0.0559 0.1496 1.0000
9.500 1.2693 0.03925 0.02958 -0.0542 0.1231 1.0000
9.750 1.2648 0.04204 0.03224 -0.0523 0.1041 1.0000
10.000 1.2582 0.04523 0.03535 -0.0507 0.0909 1.0000
10.250 1.2514 0.04870 0.03882 -0.0497 0.0807 1.0000
10.500 1.2477 0.05211 0.04235 -0.0489 0.0711 1.0000
10.750 1.2433 0.05566 0.04590 -0.0485 0.0648 1.0000
11.000 1.2432 0.05889 0.04941 -0.0480 0.0585 1.0000
11.250 1.2411 0.06229 0.05287 -0.0478 0.0550 1.0000
11.500 1.2426 0.06543 0.05617 -0.0470 0.0518 1.0000
11.750 1.2437 0.06867 0.05961 -0.0465 0.0487 1.0000
12.000 1.2427 0.07215 0.06320 -0.0466 0.0462 1.0000
12.250 1.2407 0.07569 0.06675 -0.0468 0.0443 1.0000
12.500 1.2409 0.07941 0.07075 -0.0465 0.0424 1.0000
12.750 1.2395 0.08345 0.07506 -0.0466 0.0410 1.0000
13.000 1.2361 0.08788 0.07974 -0.0471 0.0400 1.0000
13.250 1.2299 0.09284 0.08495 -0.0481 0.0393 1.0000
13.500 1.2207 0.09842 0.09077 -0.0499 0.0389 1.0000
13.750 1.2086 0.10471 0.09730 -0.0524 0.0386 1.0000
14.000 1.1934 0.11192 0.10474 -0.0559 0.0385 1.0000
14.250 1.1743 0.12049 0.11355 -0.0605 0.0388 1.0000
14.500 1.1517 0.13080 0.12407 -0.0666 0.0394 1.0000
14.750 1.1256 0.14328 0.13669 -0.0742 0.0403 1.0000
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Polar data table (+)
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