GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 200,000 Max Cl/Cd: 78.11 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe178-il-200000.txt Download as CSV file: xf-goe178-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 178 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3557 0.09205 0.08873 -0.0179 1.0000 0.0445
-7.500 -0.3507 0.08921 0.08593 -0.0193 1.0000 0.0467
-7.250 -0.3493 0.08642 0.08320 -0.0250 1.0000 0.0496
-7.000 -0.3384 0.08246 0.07924 -0.0398 1.0000 0.0506
-6.750 -0.3387 0.07800 0.07486 -0.0342 1.0000 0.0516
-6.500 -0.3323 0.07567 0.07257 -0.0310 1.0000 0.0528
-6.250 -0.3260 0.07328 0.07020 -0.0304 1.0000 0.0544
-6.000 -0.3199 0.07064 0.06759 -0.0314 1.0000 0.0566
-5.750 -0.2938 0.06614 0.06284 -0.0471 1.0000 0.0618
-5.500 -0.2928 0.06122 0.05799 -0.0463 1.0000 0.0626
-5.250 -0.2766 0.05864 0.05549 -0.0447 0.9970 0.0643
-5.000 -0.2403 0.05530 0.05210 -0.0494 0.9919 0.0691
-4.750 -0.1794 0.04723 0.04359 -0.0653 0.9854 0.0762
-4.500 -0.1456 0.04415 0.04052 -0.0684 0.9797 0.0786
-4.250 -0.0883 0.03919 0.03489 -0.0786 0.9734 0.0895
-4.000 -0.0534 0.03549 0.03130 -0.0819 0.9675 0.0917
-3.750 -0.0149 0.03272 0.02841 -0.0854 0.9586 0.0955
-3.500 0.0340 0.02537 0.01991 -0.0905 0.9481 0.0763
-3.250 0.0724 0.02094 0.01465 -0.0919 0.9350 0.0622
-3.000 0.1035 0.01865 0.01208 -0.0924 0.9166 0.0611
-2.750 0.1326 0.01701 0.01012 -0.0921 0.8937 0.0610
-2.500 0.1604 0.01581 0.00863 -0.0913 0.8673 0.0613
-2.250 0.1865 0.01474 0.00729 -0.0903 0.8365 0.0628
-2.000 0.2116 0.01412 0.00651 -0.0891 0.8018 0.0655
-1.750 0.2370 0.01365 0.00581 -0.0880 0.7644 0.0673
-1.500 0.2629 0.01326 0.00520 -0.0871 0.7240 0.0699
-1.250 0.2893 0.01300 0.00467 -0.0864 0.6867 0.0738
-1.000 0.3160 0.01264 0.00419 -0.0860 0.6567 0.0808
-0.750 0.3433 0.01237 0.00379 -0.0857 0.6339 0.0991
-0.500 0.3710 0.01218 0.00355 -0.0857 0.6156 0.1332
-0.250 0.3986 0.01214 0.00349 -0.0857 0.6006 0.1602
0.250 0.4539 0.01159 0.00352 -0.0860 0.5770 0.3793
0.500 0.4752 0.01024 0.00351 -0.0840 0.5681 1.0000
0.750 0.5032 0.01048 0.00351 -0.0839 0.5589 1.0000
1.000 0.5313 0.01065 0.00355 -0.0839 0.5489 1.0000
1.250 0.5592 0.01087 0.00361 -0.0838 0.5401 1.0000
1.500 0.5871 0.01107 0.00368 -0.0837 0.5314 1.0000
1.750 0.6151 0.01128 0.00379 -0.0837 0.5239 1.0000
2.000 0.6431 0.01149 0.00392 -0.0837 0.5173 1.0000
2.250 0.6711 0.01173 0.00407 -0.0837 0.5113 1.0000
2.500 0.6990 0.01193 0.00424 -0.0837 0.5048 1.0000
2.750 0.7269 0.01220 0.00441 -0.0836 0.4996 1.0000
3.000 0.7548 0.01240 0.00464 -0.0837 0.4935 1.0000
3.250 0.7824 0.01263 0.00481 -0.0836 0.4866 1.0000
3.500 0.8099 0.01284 0.00502 -0.0835 0.4791 1.0000
3.750 0.8373 0.01305 0.00519 -0.0834 0.4713 1.0000
4.000 0.8646 0.01327 0.00543 -0.0833 0.4639 1.0000
4.250 0.8920 0.01349 0.00565 -0.0832 0.4572 1.0000
4.500 0.9193 0.01374 0.00593 -0.0831 0.4506 1.0000
4.750 0.9464 0.01394 0.00616 -0.0830 0.4429 1.0000
5.000 0.9733 0.01417 0.00643 -0.0828 0.4350 1.0000
5.250 1.0003 0.01438 0.00667 -0.0826 0.4275 1.0000
5.500 1.0269 0.01458 0.00694 -0.0824 0.4186 1.0000
5.750 1.0531 0.01471 0.00710 -0.0821 0.4075 1.0000
6.000 1.0788 0.01477 0.00719 -0.0817 0.3940 1.0000
6.250 1.1044 0.01480 0.00729 -0.0813 0.3786 1.0000
6.500 1.1302 0.01490 0.00749 -0.0809 0.3647 1.0000
6.750 1.1560 0.01499 0.00770 -0.0806 0.3477 1.0000
7.000 1.1810 0.01512 0.00785 -0.0801 0.3222 1.0000
7.250 1.2043 0.01548 0.00810 -0.0795 0.2804 1.0000
7.500 1.2210 0.01678 0.00894 -0.0782 0.2009 1.0000
7.750 1.2214 0.02049 0.01168 -0.0753 0.0521 1.0000
8.000 1.2374 0.02197 0.01328 -0.0738 0.0407 1.0000
8.250 1.2531 0.02329 0.01470 -0.0723 0.0359 1.0000
8.500 1.2659 0.02477 0.01632 -0.0704 0.0335 1.0000
8.750 1.2789 0.02612 0.01778 -0.0685 0.0317 1.0000
9.000 1.2904 0.02750 0.01925 -0.0665 0.0300 1.0000
9.250 1.3004 0.02890 0.02072 -0.0645 0.0284 1.0000
9.500 1.3012 0.03087 0.02272 -0.0614 0.0270 1.0000
9.750 1.3042 0.03275 0.02467 -0.0585 0.0263 1.0000
10.000 1.3110 0.03450 0.02652 -0.0562 0.0259 1.0000
10.250 1.3195 0.03637 0.02847 -0.0542 0.0254 1.0000
10.500 1.3305 0.03831 0.03050 -0.0523 0.0250 1.0000
10.750 1.3452 0.04038 0.03268 -0.0506 0.0247 1.0000
11.000 1.3637 0.04270 0.03516 -0.0493 0.0245 1.0000
11.250 1.3820 0.04530 0.03793 -0.0481 0.0244 1.0000
11.500 1.3931 0.04777 0.04061 -0.0465 0.0239 1.0000
11.750 1.4003 0.05031 0.04336 -0.0449 0.0234 1.0000
12.000 1.4053 0.05331 0.04661 -0.0432 0.0232 1.0000
12.250 1.4075 0.05724 0.05085 -0.0414 0.0238 1.0000
12.500 1.4040 0.06133 0.05523 -0.0398 0.0244 1.0000
12.750 1.3965 0.06562 0.05977 -0.0385 0.0249 1.0000
13.000 1.3868 0.07023 0.06461 -0.0376 0.0255 1.0000
13.250 1.4031 0.07472 0.06922 -0.0367 0.0274 1.0000
13.500 1.3470 0.08126 0.07643 -0.0378 0.0296 1.0000
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Polar data table (+)
Polar graphs
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