GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 367 AIRFOIL (goe367-il) Reynolds number: 100,000 Max Cl/Cd: 47.66 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe367-il-100000-n5.txt Download as CSV file: xf-goe367-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 367 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2225 0.09515 0.08966 -0.0832 0.9611 0.0605
-10.000 -0.2175 0.08998 0.08448 -0.0879 0.9557 0.0610
-9.750 -0.2184 0.08469 0.07917 -0.0921 0.9476 0.0611
-9.500 -0.2226 0.07813 0.07261 -0.0981 0.9401 0.0610
-9.250 -0.2493 0.06877 0.06320 -0.1065 0.9268 0.0602
-9.000 -0.2951 0.05966 0.05382 -0.1097 0.9115 0.0596
-8.750 -0.3180 0.05305 0.04685 -0.1100 0.9022 0.0596
-8.500 -0.3312 0.04858 0.04203 -0.1081 0.8918 0.0599
-8.250 -0.3290 0.04478 0.03783 -0.1073 0.8859 0.0608
-8.000 -0.3307 0.04195 0.03465 -0.1045 0.8761 0.0618
-7.750 -0.3230 0.03843 0.03056 -0.1032 0.8707 0.0632
-7.500 -0.3177 0.03578 0.02737 -0.1005 0.8623 0.0642
-7.250 -0.2995 0.03399 0.02530 -0.0995 0.8563 0.0650
-7.000 -0.2739 0.03275 0.02392 -0.0996 0.8523 0.0659
-6.750 -0.2569 0.03184 0.02289 -0.0981 0.8448 0.0669
-6.500 -0.2345 0.03083 0.02170 -0.0974 0.8390 0.0684
-6.250 -0.2085 0.02957 0.02017 -0.0973 0.8350 0.0706
-6.000 -0.1882 0.02841 0.01867 -0.0961 0.8287 0.0725
-5.750 -0.1652 0.02774 0.01799 -0.0954 0.8225 0.0739
-5.500 -0.1375 0.02698 0.01716 -0.0955 0.8182 0.0755
-5.250 -0.1106 0.02624 0.01630 -0.0953 0.8136 0.0778
-5.000 -0.0898 0.02567 0.01557 -0.0941 0.8062 0.0806
-4.750 -0.0626 0.02507 0.01494 -0.0940 0.8014 0.0833
-4.500 -0.0323 0.02447 0.01429 -0.0943 0.7977 0.0864
-4.250 -0.0124 0.02410 0.01385 -0.0929 0.7898 0.0896
-4.000 0.0141 0.02361 0.01332 -0.0926 0.7843 0.0935
-3.750 0.0441 0.02312 0.01279 -0.0929 0.7802 0.0987
-3.500 0.0656 0.02281 0.01243 -0.0917 0.7728 0.1039
-3.250 0.0910 0.02246 0.01211 -0.0913 0.7667 0.1097
-3.000 0.1209 0.02196 0.01155 -0.0914 0.7623 0.1184
-2.750 0.1422 0.02177 0.01140 -0.0903 0.7546 0.1268
-2.500 0.1676 0.02142 0.01105 -0.0898 0.7482 0.1365
-2.250 0.1979 0.02099 0.01056 -0.0900 0.7435 0.1487
-2.000 0.2177 0.02087 0.01048 -0.0886 0.7348 0.1588
-1.750 0.2445 0.02051 0.01014 -0.0883 0.7284 0.1707
-1.500 0.2714 0.02022 0.00983 -0.0880 0.7220 0.1837
-1.250 0.2936 0.02005 0.00972 -0.0869 0.7133 0.1997
-1.000 0.3230 0.01959 0.00934 -0.0871 0.7074 0.2243
-0.500 0.3685 0.01863 0.00908 -0.0853 0.6909 0.3771
-0.250 0.4125 0.01764 0.00969 -0.0867 0.6833 0.8420
0.000 0.4401 0.01786 0.00982 -0.0857 0.6751 0.9176
0.250 0.5028 0.01804 0.00982 -0.0920 0.6674 0.9583
0.500 0.5806 0.01806 0.00969 -0.1020 0.6578 0.9849
0.750 0.6441 0.01796 0.00942 -0.1094 0.6492 1.0000
1.000 0.6641 0.01803 0.00941 -0.1080 0.6400 1.0000
1.250 0.6851 0.01809 0.00936 -0.1068 0.6317 1.0000
1.500 0.7047 0.01818 0.00938 -0.1054 0.6224 1.0000
1.750 0.7250 0.01826 0.00937 -0.1040 0.6137 1.0000
2.000 0.7446 0.01836 0.00940 -0.1026 0.6047 1.0000
2.250 0.7641 0.01849 0.00945 -0.1011 0.5960 1.0000
2.500 0.7837 0.01861 0.00949 -0.0996 0.5874 1.0000
2.750 0.8031 0.01876 0.00957 -0.0981 0.5793 1.0000
3.000 0.8218 0.01892 0.00967 -0.0964 0.5709 1.0000
3.250 0.8414 0.01907 0.00975 -0.0949 0.5631 1.0000
3.500 0.8587 0.01928 0.00992 -0.0931 0.5545 1.0000
3.750 0.8791 0.01944 0.00998 -0.0917 0.5472 1.0000
4.000 0.8946 0.01971 0.01023 -0.0895 0.5386 1.0000
4.250 0.9162 0.01986 0.01029 -0.0884 0.5319 1.0000
4.500 0.9303 0.02018 0.01062 -0.0860 0.5239 1.0000
4.750 0.9491 0.02042 0.01080 -0.0844 0.5172 1.0000
5.000 0.9680 0.02069 0.01103 -0.0829 0.5108 1.0000
5.250 0.9829 0.02102 0.01137 -0.0807 0.5038 1.0000
5.500 1.0036 0.02127 0.01156 -0.0795 0.4980 1.0000
5.750 1.0200 0.02162 0.01191 -0.0776 0.4917 1.0000
6.000 1.0351 0.02196 0.01227 -0.0755 0.4846 1.0000
6.250 1.0580 0.02220 0.01242 -0.0747 0.4786 1.0000
6.500 1.0686 0.02265 0.01293 -0.0719 0.4710 1.0000
6.750 1.0863 0.02298 0.01324 -0.0702 0.4643 1.0000
7.000 1.1051 0.02333 0.01357 -0.0689 0.4582 1.0000
7.250 1.1180 0.02379 0.01409 -0.0666 0.4515 1.0000
7.500 1.1371 0.02413 0.01442 -0.0653 0.4458 1.0000
7.750 1.1535 0.02456 0.01486 -0.0636 0.4403 1.0000
8.000 1.1649 0.02508 0.01545 -0.0611 0.4341 1.0000
8.250 1.1831 0.02546 0.01583 -0.0598 0.4285 1.0000
8.500 1.1976 0.02597 0.01638 -0.0580 0.4227 1.0000
8.750 1.2086 0.02658 0.01707 -0.0557 0.4164 1.0000
9.000 1.2270 0.02702 0.01753 -0.0545 0.4113 1.0000
9.250 1.2438 0.02758 0.01813 -0.0532 0.4067 1.0000
9.500 1.2542 0.02836 0.01904 -0.0512 0.4015 1.0000
9.750 1.2692 0.02898 0.01973 -0.0497 0.3965 1.0000
10.000 1.2913 0.02936 0.02009 -0.0492 0.3922 1.0000
10.250 1.2966 0.03040 0.02130 -0.0467 0.3868 1.0000
10.500 1.3064 0.03127 0.02228 -0.0448 0.3811 1.0000
10.750 1.3247 0.03174 0.02275 -0.0439 0.3758 1.0000
11.000 1.3289 0.03296 0.02412 -0.0416 0.3700 1.0000
11.250 1.3364 0.03406 0.02534 -0.0398 0.3644 1.0000
11.500 1.3520 0.03471 0.02603 -0.0387 0.3593 1.0000
11.750 1.3551 0.03612 0.02760 -0.0367 0.3532 1.0000
12.000 1.3578 0.03758 0.02918 -0.0347 0.3464 1.0000
12.250 1.3722 0.03827 0.02987 -0.0336 0.3402 1.0000
12.500 1.3656 0.04056 0.03239 -0.0314 0.3332 1.0000
12.750 1.3709 0.04199 0.03391 -0.0299 0.3264 1.0000
13.000 1.3701 0.04398 0.03602 -0.0283 0.3189 1.0000
13.250 1.3663 0.04626 0.03842 -0.0267 0.3102 1.0000
13.500 1.3598 0.04895 0.04124 -0.0253 0.3008 1.0000
13.750 1.3576 0.05126 0.04358 -0.0241 0.2902 1.0000
14.000 1.3391 0.05566 0.04819 -0.0230 0.2793 1.0000
14.250 1.3240 0.05990 0.05256 -0.0224 0.2672 1.0000
14.500 1.3063 0.06472 0.05749 -0.0220 0.2533 1.0000
14.750 1.2875 0.06994 0.06280 -0.0220 0.2365 1.0000
15.000 1.2758 0.07424 0.06706 -0.0221 0.2146 1.0000
15.250 1.2664 0.07813 0.07075 -0.0220 0.1920 1.0000
15.500 1.2529 0.08268 0.07512 -0.0221 0.1767 1.0000
15.750 1.2400 0.08735 0.07970 -0.0224 0.1647 1.0000
16.000 1.2297 0.09178 0.08410 -0.0228 0.1544 1.0000
16.250 1.2209 0.09602 0.08829 -0.0233 0.1449 1.0000
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