GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 50,000 Max Cl/Cd: 26.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe681-il-50000-n5.txt Download as CSV file: xf-goe681-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 681 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3020 0.11188 0.10462 -0.0437 1.0000 0.0823
-10.000 -0.3162 0.10956 0.10240 -0.0422 1.0000 0.0819
-9.750 -0.3322 0.10719 0.10013 -0.0407 1.0000 0.0814
-9.500 -0.3319 0.10219 0.09515 -0.0446 0.9947 0.0815
-9.250 -0.3310 0.09602 0.08898 -0.0503 0.9865 0.0820
-9.000 -0.3352 0.08920 0.08215 -0.0566 0.9780 0.0822
-8.750 -0.3584 0.07898 0.07190 -0.0658 0.9675 0.0822
-8.500 -0.4204 0.06664 0.05930 -0.0748 0.9496 0.0810
-8.250 -0.4473 0.05932 0.05156 -0.0780 0.9359 0.0810
-8.000 -0.4562 0.05442 0.04623 -0.0788 0.9246 0.0818
-7.750 -0.4586 0.05077 0.04216 -0.0782 0.9140 0.0827
-7.500 -0.4480 0.04718 0.03802 -0.0788 0.9063 0.0839
-7.250 -0.4389 0.04489 0.03538 -0.0776 0.8970 0.0851
-7.000 -0.4158 0.04344 0.03386 -0.0778 0.8900 0.0868
-6.750 -0.3885 0.04182 0.03205 -0.0788 0.8846 0.0894
-6.500 -0.3781 0.04050 0.03046 -0.0768 0.8745 0.0922
-6.250 -0.3498 0.03915 0.02899 -0.0776 0.8690 0.0960
-6.000 -0.3305 0.03823 0.02798 -0.0767 0.8613 0.0998
-5.750 -0.3098 0.03708 0.02661 -0.0759 0.8534 0.1044
-5.500 -0.2779 0.03607 0.02560 -0.0769 0.8486 0.1105
-5.250 -0.2625 0.03545 0.02494 -0.0751 0.8399 0.1169
-5.000 -0.2388 0.03479 0.02424 -0.0747 0.8328 0.1270
-4.750 -0.2050 0.03418 0.02368 -0.0758 0.8281 0.1413
-4.500 -0.1927 0.03409 0.02358 -0.0734 0.8186 0.1536
-4.250 -0.1670 0.03390 0.02336 -0.0731 0.8117 0.1707
-4.000 -0.1322 0.03373 0.02301 -0.0742 0.8072 0.1972
-3.750 -0.1257 0.03405 0.02340 -0.0709 0.7965 0.2120
-3.500 -0.0981 0.03390 0.02317 -0.0709 0.7902 0.2345
-3.250 -0.0604 0.03336 0.02258 -0.0722 0.7862 0.2543
-3.000 -0.0546 0.03349 0.02271 -0.0688 0.7748 0.2641
-2.750 -0.0210 0.03308 0.02216 -0.0695 0.7691 0.2814
-2.500 0.0149 0.03264 0.02165 -0.0705 0.7641 0.2984
-2.250 0.0256 0.03276 0.02181 -0.0678 0.7526 0.3092
-2.000 0.0664 0.03218 0.02118 -0.0694 0.7472 0.3288
-1.750 0.0824 0.03222 0.02115 -0.0674 0.7356 0.3434
-1.500 0.1208 0.03159 0.02050 -0.0685 0.7284 0.3626
-1.250 0.1421 0.03141 0.02037 -0.0671 0.7177 0.3769
-1.000 0.1762 0.03086 0.01983 -0.0674 0.7095 0.3958
-0.750 0.2015 0.03058 0.01959 -0.0666 0.7000 0.4146
-0.500 0.2287 0.03020 0.01929 -0.0660 0.6908 0.4390
-0.250 0.2601 0.02963 0.01886 -0.0659 0.6833 0.4741
0.000 0.2771 0.02944 0.01889 -0.0638 0.6722 0.5170
0.250 0.3161 0.02825 0.01826 -0.0640 0.6668 0.6263
0.500 0.3987 0.02787 0.01854 -0.0723 0.6539 0.8958
0.750 0.5002 0.02734 0.01771 -0.0848 0.6445 1.0000
1.000 0.5124 0.02749 0.01768 -0.0820 0.6326 1.0000
1.250 0.5264 0.02763 0.01765 -0.0795 0.6210 1.0000
1.500 0.5527 0.02741 0.01723 -0.0786 0.6110 1.0000
1.750 0.5607 0.02776 0.01746 -0.0752 0.5977 1.0000
2.000 0.5854 0.02762 0.01713 -0.0741 0.5871 1.0000
2.250 0.6007 0.02778 0.01716 -0.0717 0.5746 1.0000
2.500 0.6132 0.02805 0.01731 -0.0689 0.5615 1.0000
2.750 0.6404 0.02788 0.01695 -0.0682 0.5507 1.0000
3.000 0.6521 0.02821 0.01718 -0.0653 0.5371 1.0000
3.250 0.6658 0.02853 0.01740 -0.0628 0.5241 1.0000
3.500 0.6916 0.02849 0.01717 -0.0619 0.5130 1.0000
3.750 0.7041 0.02891 0.01749 -0.0593 0.5000 1.0000
4.000 0.7186 0.02931 0.01779 -0.0571 0.4877 1.0000
4.250 0.7466 0.02930 0.01758 -0.0565 0.4777 1.0000
4.500 0.7534 0.03001 0.01824 -0.0534 0.4655 1.0000
4.750 0.7736 0.03032 0.01841 -0.0520 0.4556 1.0000
5.000 0.7892 0.03081 0.01882 -0.0500 0.4454 1.0000
5.250 0.8061 0.03133 0.01923 -0.0483 0.4362 1.0000
5.500 0.8236 0.03185 0.01966 -0.0467 0.4273 1.0000
5.750 0.8429 0.03239 0.02011 -0.0454 0.4195 1.0000
6.000 0.8560 0.03314 0.02083 -0.0435 0.4113 1.0000
6.250 0.8852 0.03338 0.02089 -0.0434 0.4047 1.0000
6.500 0.8888 0.03456 0.02214 -0.0405 0.3969 1.0000
6.750 0.9111 0.03509 0.02258 -0.0397 0.3906 1.0000
7.000 0.9322 0.03575 0.02317 -0.0389 0.3850 1.0000
7.250 0.9375 0.03704 0.02454 -0.0364 0.3787 1.0000
7.500 0.9582 0.03773 0.02519 -0.0356 0.3734 1.0000
7.750 0.9903 0.03804 0.02537 -0.0360 0.3689 1.0000
8.000 0.9824 0.03999 0.02748 -0.0325 0.3632 1.0000
8.250 0.9920 0.04126 0.02879 -0.0308 0.3581 1.0000
8.500 1.0172 0.04183 0.02931 -0.0305 0.3540 1.0000
8.750 1.0398 0.04264 0.03008 -0.0300 0.3503 1.0000
9.000 1.0169 0.04579 0.03345 -0.0262 0.3454 1.0000
9.250 1.0112 0.04825 0.03603 -0.0240 0.3408 1.0000
9.500 1.0279 0.04936 0.03714 -0.0232 0.3372 1.0000
9.750 1.0629 0.04935 0.03708 -0.0235 0.3343 1.0000
10.000 0.9337 0.06260 0.05077 -0.0188 0.3249 1.0000
10.250 0.9164 0.06754 0.05579 -0.0185 0.3196 1.0000
10.500 0.9357 0.06848 0.05674 -0.0179 0.3173 1.0000
10.750 0.9651 0.06833 0.05658 -0.0172 0.3157 1.0000
11.250 0.8380 0.09233 0.08087 -0.0217 0.2980 1.0000
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Polar data table (+)
Polar graphs
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