GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 100,000 Max Cl/Cd: 62.13 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe240-il-100000.txt Download as CSV file: xf-goe240-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3235 0.10386 0.09914 -0.0280 1.0000 0.0589
-7.750 -0.3309 0.10348 0.09887 -0.0303 1.0000 0.0593
-7.500 -0.3320 0.10262 0.09809 -0.0344 1.0000 0.0596
-7.250 -0.3255 0.09574 0.09126 -0.0285 1.0000 0.0607
-7.000 -0.3184 0.09181 0.08736 -0.0249 1.0000 0.0629
-6.750 -0.3182 0.08957 0.08519 -0.0239 1.0000 0.0651
-6.500 -0.3205 0.08768 0.08337 -0.0234 1.0000 0.0672
-6.250 -0.3249 0.08619 0.08197 -0.0233 1.0000 0.0693
-6.000 -0.3293 0.08561 0.08144 -0.0254 1.0000 0.0711
-5.750 -0.3206 0.08592 0.08164 -0.0337 1.0000 0.0722
-5.500 -0.3211 0.08165 0.07745 -0.0318 1.0000 0.0728
-5.250 -0.3247 0.07790 0.07378 -0.0269 1.0000 0.0739
-5.000 -0.3230 0.07515 0.07107 -0.0246 1.0000 0.0755
-4.750 -0.3160 0.07262 0.06854 -0.0245 1.0000 0.0780
-4.500 -0.3022 0.07001 0.06588 -0.0269 1.0000 0.0819
-4.250 -0.2547 0.06538 0.06105 -0.0385 0.9957 0.0874
-4.000 -0.2282 0.06168 0.05734 -0.0406 0.9906 0.0932
-3.750 -0.1736 0.05723 0.05261 -0.0517 0.9849 0.1016
-3.500 -0.1423 0.05388 0.04921 -0.0549 0.9791 0.1079
-3.250 -0.0955 0.05008 0.04519 -0.0623 0.9732 0.1173
-3.000 -0.0530 0.04698 0.04190 -0.0680 0.9676 0.1313
-2.750 -0.0126 0.04418 0.03890 -0.0727 0.9607 0.1458
-2.500 0.0318 0.04133 0.03591 -0.0778 0.9563 0.1624
-2.250 0.0684 0.03968 0.03401 -0.0811 0.9476 0.1889
-2.000 0.1078 0.03700 0.03133 -0.0847 0.9428 0.2203
-1.750 0.1368 0.03514 0.02947 -0.0860 0.9340 0.2553
-1.000 0.3049 0.02713 0.01929 -0.0997 0.9161 0.1160
-0.750 0.3479 0.02561 0.01744 -0.1019 0.9076 0.1099
-0.500 0.4007 0.02374 0.01513 -0.1054 0.9008 0.1023
-0.250 0.4408 0.02258 0.01372 -0.1067 0.8899 0.1008
0.000 0.4824 0.02127 0.01236 -0.1084 0.8816 0.1027
0.250 0.5201 0.02026 0.01137 -0.1095 0.8727 0.1085
0.500 0.5522 0.01945 0.01063 -0.1096 0.8619 0.1192
0.750 0.5864 0.01858 0.00980 -0.1098 0.8526 0.1348
1.000 0.6225 0.01585 0.00898 -0.1103 0.8438 1.0000
1.250 0.6517 0.01582 0.00866 -0.1097 0.8310 1.0000
1.500 0.6803 0.01583 0.00850 -0.1090 0.8180 1.0000
1.750 0.7082 0.01587 0.00840 -0.1083 0.8046 1.0000
2.000 0.7353 0.01597 0.00839 -0.1074 0.7907 1.0000
2.250 0.7616 0.01611 0.00843 -0.1065 0.7762 1.0000
2.500 0.7872 0.01623 0.00848 -0.1054 0.7605 1.0000
2.750 0.8124 0.01628 0.00845 -0.1041 0.7434 1.0000
3.000 0.8377 0.01624 0.00831 -0.1027 0.7254 1.0000
3.250 0.8628 0.01615 0.00813 -0.1012 0.7066 1.0000
3.500 0.8863 0.01613 0.00808 -0.0997 0.6851 1.0000
3.750 0.9114 0.01610 0.00799 -0.0985 0.6660 1.0000
4.000 0.9367 0.01611 0.00795 -0.0975 0.6475 1.0000
4.250 0.9609 0.01621 0.00806 -0.0964 0.6262 1.0000
4.500 0.9860 0.01629 0.00807 -0.0953 0.6061 1.0000
4.750 1.0103 0.01647 0.00821 -0.0943 0.5833 1.0000
5.000 1.0348 0.01668 0.00828 -0.0931 0.5604 1.0000
5.250 1.0580 0.01703 0.00858 -0.0920 0.5344 1.0000
5.500 1.0809 0.01745 0.00891 -0.0908 0.5083 1.0000
5.750 1.1032 0.01789 0.00927 -0.0896 0.4819 1.0000
6.000 1.1251 0.01832 0.00962 -0.0884 0.4553 1.0000
6.250 1.1464 0.01876 0.01007 -0.0871 0.4282 1.0000
6.500 1.1675 0.01926 0.01055 -0.0859 0.4015 1.0000
6.750 1.1884 0.01988 0.01110 -0.0846 0.3765 1.0000
7.000 1.2093 0.02063 0.01171 -0.0834 0.3541 1.0000
7.250 1.2299 0.02143 0.01252 -0.0823 0.3319 1.0000
7.500 1.2502 0.02222 0.01325 -0.0811 0.3121 1.0000
7.750 1.2697 0.02296 0.01396 -0.0799 0.2932 1.0000
8.000 1.2883 0.02359 0.01468 -0.0785 0.2747 1.0000
8.250 1.3072 0.02423 0.01540 -0.0772 0.2587 1.0000
8.500 1.3262 0.02488 0.01619 -0.0760 0.2449 1.0000
8.750 1.3423 0.02543 0.01685 -0.0743 0.2273 1.0000
9.000 1.3562 0.02605 0.01751 -0.0725 0.2065 1.0000
9.250 1.3700 0.02679 0.01839 -0.0706 0.1845 1.0000
9.500 1.3780 0.02797 0.01955 -0.0681 0.1471 1.0000
9.750 1.3755 0.03037 0.02141 -0.0643 0.0770 1.0000
10.000 1.3680 0.03292 0.02370 -0.0600 0.0643 1.0000
10.250 1.3638 0.03528 0.02617 -0.0564 0.0580 1.0000
10.500 1.3556 0.03804 0.02895 -0.0530 0.0544 1.0000
10.750 1.3555 0.04039 0.03145 -0.0503 0.0518 1.0000
11.000 1.3582 0.04269 0.03390 -0.0480 0.0493 1.0000
11.250 1.3628 0.04504 0.03634 -0.0459 0.0471 1.0000
11.500 1.3703 0.04746 0.03878 -0.0441 0.0450 1.0000
11.750 1.3917 0.05060 0.04182 -0.0426 0.0422 1.0000
12.000 1.3955 0.05281 0.04433 -0.0409 0.0409 1.0000
12.250 1.4020 0.05540 0.04721 -0.0394 0.0396 1.0000
12.500 1.4092 0.05838 0.05046 -0.0379 0.0389 1.0000
12.750 1.4118 0.06169 0.05406 -0.0364 0.0384 1.0000
13.000 1.4096 0.06532 0.05798 -0.0352 0.0382 1.0000
13.250 1.4028 0.06928 0.06225 -0.0342 0.0381 1.0000
13.500 1.3919 0.07363 0.06690 -0.0336 0.0382 1.0000
13.750 1.3774 0.07840 0.07196 -0.0336 0.0383 1.0000
14.000 1.3603 0.08362 0.07746 -0.0343 0.0385 1.0000
14.250 1.3409 0.08936 0.08347 -0.0357 0.0387 1.0000
14.500 1.3197 0.09567 0.09003 -0.0380 0.0390 1.0000
14.750 1.2973 0.10259 0.09719 -0.0412 0.0393 1.0000
15.000 1.2737 0.11026 0.10507 -0.0454 0.0397 1.0000
15.250 1.2494 0.11879 0.11379 -0.0506 0.0401 1.0000
15.500 1.2244 0.12831 0.12348 -0.0568 0.0406 1.0000
15.750 1.1993 0.13880 0.13411 -0.0639 0.0412 1.0000
16.000 1.1767 0.14961 0.14499 -0.0708 0.0419 1.0000
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Polar data table (+)
Polar graphs
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