GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 50,000 Max Cl/Cd: 38.56 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe401-il-50000-n5.txt Download as CSV file: xf-goe401-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3311 0.10857 0.10164 -0.0240 1.0000 0.0925
-8.000 -0.3380 0.10780 0.10101 -0.0255 1.0000 0.0929
-7.750 -0.3401 0.10678 0.10007 -0.0288 1.0000 0.0932
-7.500 -0.3219 0.09909 0.09239 -0.0237 1.0000 0.0951
-7.250 -0.3146 0.09563 0.08897 -0.0226 1.0000 0.0973
-7.000 -0.3104 0.09297 0.08639 -0.0224 1.0000 0.1002
-6.750 -0.3084 0.09077 0.08427 -0.0231 1.0000 0.1037
-6.500 -0.3085 0.08963 0.08322 -0.0264 1.0000 0.1072
-6.250 -0.3056 0.08924 0.08283 -0.0318 1.0000 0.1083
-6.000 -0.3009 0.08414 0.07788 -0.0277 1.0000 0.1099
-5.750 -0.2966 0.08103 0.07485 -0.0255 1.0000 0.1120
-5.500 -0.2931 0.07859 0.07247 -0.0247 1.0000 0.1144
-5.250 -0.2898 0.07643 0.07034 -0.0246 1.0000 0.1174
-5.000 -0.2833 0.07500 0.06887 -0.0270 1.0000 0.1218
-4.750 -0.2720 0.07377 0.06752 -0.0308 1.0000 0.1235
-4.500 -0.2707 0.07017 0.06403 -0.0278 1.0000 0.1248
-4.250 -0.2505 0.06654 0.06042 -0.0290 0.9943 0.1294
-4.000 -0.2037 0.06287 0.05652 -0.0382 0.9811 0.1401
-3.750 -0.1693 0.05915 0.05271 -0.0422 0.9688 0.1473
-3.250 -0.0951 0.05264 0.04587 -0.0521 0.9452 0.1603
-3.000 -0.0280 0.04787 0.04019 -0.0616 0.9357 0.0925
-2.750 0.0038 0.04471 0.03696 -0.0640 0.9239 0.0900
-2.500 0.0413 0.04200 0.03400 -0.0670 0.9125 0.0883
-2.250 0.0836 0.03914 0.03080 -0.0706 0.9028 0.0840
-2.000 0.1299 0.03657 0.02750 -0.0737 0.8921 0.0780
-1.750 0.1648 0.03441 0.02511 -0.0754 0.8795 0.0771
-1.500 0.2008 0.03249 0.02291 -0.0770 0.8667 0.0764
-1.250 0.2373 0.03073 0.02082 -0.0783 0.8537 0.0762
-1.000 0.2739 0.02927 0.01891 -0.0793 0.8399 0.0780
-0.750 0.3065 0.02797 0.01751 -0.0800 0.8247 0.0807
-0.500 0.3396 0.02683 0.01613 -0.0804 0.8088 0.0820
-0.250 0.3717 0.02578 0.01482 -0.0806 0.7917 0.0832
0.000 0.4027 0.02488 0.01367 -0.0803 0.7742 0.0850
0.250 0.4371 0.02407 0.01256 -0.0806 0.7562 0.0879
0.500 0.4698 0.02337 0.01155 -0.0805 0.7378 0.0925
0.750 0.4993 0.02291 0.01105 -0.0802 0.7193 0.1008
1.000 0.5273 0.02249 0.01049 -0.0795 0.7008 0.1114
1.250 0.5534 0.02215 0.01006 -0.0786 0.6813 0.1255
1.500 0.5798 0.02180 0.00970 -0.0779 0.6629 0.1583
1.750 0.6060 0.02113 0.00939 -0.0777 0.6453 0.2624
2.000 0.6483 0.01972 0.00908 -0.0800 0.6273 1.0000
2.250 0.6738 0.02001 0.00907 -0.0792 0.6110 1.0000
2.500 0.6991 0.02032 0.00914 -0.0783 0.5955 1.0000
2.750 0.7242 0.02066 0.00928 -0.0775 0.5806 1.0000
3.000 0.7491 0.02102 0.00949 -0.0768 0.5665 1.0000
3.250 0.7741 0.02139 0.00973 -0.0760 0.5531 1.0000
3.500 0.7990 0.02179 0.01000 -0.0753 0.5406 1.0000
3.750 0.8242 0.02218 0.01029 -0.0746 0.5289 1.0000
4.000 0.8489 0.02261 0.01064 -0.0739 0.5173 1.0000
4.250 0.8728 0.02310 0.01110 -0.0731 0.5056 1.0000
4.500 0.8973 0.02359 0.01157 -0.0724 0.4950 1.0000
4.750 0.9225 0.02405 0.01196 -0.0718 0.4852 1.0000
5.000 0.9454 0.02464 0.01261 -0.0710 0.4743 1.0000
5.250 0.9695 0.02521 0.01319 -0.0703 0.4647 1.0000
5.500 0.9938 0.02577 0.01377 -0.0695 0.4553 1.0000
5.750 1.0162 0.02646 0.01457 -0.0687 0.4455 1.0000
6.000 1.0412 0.02705 0.01514 -0.0681 0.4373 1.0000
6.250 1.0624 0.02782 0.01611 -0.0672 0.4274 1.0000
6.500 1.0858 0.02853 0.01689 -0.0664 0.4193 1.0000
6.750 1.1075 0.02932 0.01784 -0.0655 0.4104 1.0000
7.000 1.1295 0.03014 0.01880 -0.0647 0.4024 1.0000
7.250 1.1511 0.03098 0.01983 -0.0638 0.3941 1.0000
7.500 1.1718 0.03191 0.02094 -0.0628 0.3864 1.0000
7.750 1.1926 0.03274 0.02195 -0.0618 0.3779 1.0000
8.000 1.2105 0.03365 0.02309 -0.0605 0.3685 1.0000
8.250 1.2341 0.03408 0.02362 -0.0595 0.3594 1.0000
8.500 1.2478 0.03494 0.02476 -0.0576 0.3474 1.0000
8.750 1.2630 0.03559 0.02564 -0.0558 0.3354 1.0000
9.000 1.2788 0.03608 0.02632 -0.0540 0.3234 1.0000
9.250 1.2947 0.03646 0.02691 -0.0521 0.3112 1.0000
9.500 1.3068 0.03684 0.02748 -0.0497 0.2970 1.0000
9.750 1.3146 0.03737 0.02823 -0.0470 0.2811 1.0000
10.000 1.3204 0.03808 0.02916 -0.0442 0.2649 1.0000
10.250 1.3223 0.03896 0.03022 -0.0411 0.2465 1.0000
10.500 1.3179 0.03988 0.03114 -0.0373 0.2249 1.0000
10.750 1.3076 0.04167 0.03299 -0.0339 0.2002 1.0000
11.000 1.2963 0.04403 0.03533 -0.0313 0.1742 1.0000
11.250 1.2832 0.04713 0.03833 -0.0297 0.1487 1.0000
11.500 1.2685 0.05092 0.04205 -0.0290 0.1284 1.0000
11.750 1.2535 0.05525 0.04629 -0.0290 0.1144 1.0000
12.000 1.2386 0.05997 0.05096 -0.0295 0.1039 1.0000
12.250 1.2245 0.06487 0.05583 -0.0304 0.0963 1.0000
12.500 1.2113 0.06987 0.06082 -0.0315 0.0903 1.0000
12.750 1.1994 0.07484 0.06576 -0.0326 0.0846 1.0000
13.000 1.1892 0.07964 0.07058 -0.0337 0.0793 1.0000
13.250 1.1800 0.08427 0.07513 -0.0346 0.0748 1.0000
13.500 1.1740 0.08863 0.07960 -0.0354 0.0699 1.0000
13.750 1.1692 0.09269 0.08364 -0.0361 0.0659 1.0000
14.000 1.1679 0.09625 0.08723 -0.0362 0.0625 1.0000
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Polar data table (+)
Polar graphs
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