GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 100,000 Max Cl/Cd: 58.9 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe381-il-100000.txt Download as CSV file: xf-goe381-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2796 0.09684 0.09250 -0.0225 1.0000 0.0408
-7.000 -0.2821 0.09607 0.09182 -0.0234 1.0000 0.0415
-6.750 -0.2852 0.09584 0.09167 -0.0249 1.0000 0.0420
-6.500 -0.2857 0.09566 0.09154 -0.0272 1.0000 0.0423
-6.250 -0.2815 0.09517 0.09105 -0.0300 1.0000 0.0425
-6.000 -0.2828 0.09056 0.08654 -0.0277 1.0000 0.0430
-5.750 -0.2879 0.08553 0.08159 -0.0220 1.0000 0.0440
-5.500 -0.2877 0.08276 0.07888 -0.0202 1.0000 0.0450
-5.250 -0.2851 0.08035 0.07651 -0.0198 1.0000 0.0462
-5.000 -0.2801 0.07801 0.07419 -0.0201 1.0000 0.0476
-4.750 -0.2726 0.07566 0.07186 -0.0211 1.0000 0.0493
-4.500 -0.2614 0.07336 0.06955 -0.0230 1.0000 0.0514
-4.250 -0.1804 0.07196 0.06771 -0.0424 0.9932 0.0550
-4.000 -0.1685 0.06466 0.06058 -0.0420 0.9873 0.0568
-3.750 -0.1288 0.06032 0.05618 -0.0480 0.9802 0.0612
-3.500 -0.0614 0.05686 0.05239 -0.0604 0.9717 0.0687
-3.250 -0.0301 0.05242 0.04797 -0.0639 0.9634 0.0742
-3.000 0.0357 0.04925 0.04439 -0.0741 0.9563 0.0823
-2.750 0.0699 0.04533 0.04046 -0.0777 0.9464 0.0885
-2.500 0.1265 0.04182 0.03669 -0.0852 0.9410 0.0994
-2.250 0.1715 0.03906 0.03369 -0.0899 0.9302 0.1114
-2.000 0.2196 0.03628 0.03064 -0.0948 0.9216 0.1243
-1.750 0.2687 0.03352 0.02765 -0.0997 0.9144 0.1415
-1.500 0.3090 0.03147 0.02533 -0.1028 0.9030 0.1752
-1.000 0.3800 0.02655 0.02026 -0.1066 0.8814 0.2650
-0.750 0.4158 0.02484 0.01835 -0.1073 0.8691 0.3018
-0.500 0.4458 0.02308 0.01647 -0.1069 0.8531 0.3213
-0.250 0.4819 0.02232 0.01523 -0.1065 0.8362 0.2873
0.000 0.5234 0.02226 0.01435 -0.1048 0.8207 0.1577
0.250 0.5548 0.02154 0.01320 -0.1032 0.8058 0.1195
0.500 0.5825 0.02047 0.01197 -0.1022 0.7916 0.1138
0.750 0.6099 0.01987 0.01117 -0.1013 0.7773 0.1179
1.000 0.6370 0.01917 0.01034 -0.1003 0.7629 0.1168
1.250 0.6638 0.01857 0.00962 -0.0993 0.7486 0.1169
1.500 0.6905 0.01810 0.00903 -0.0983 0.7344 0.1197
1.750 0.7157 0.01749 0.00843 -0.0971 0.7204 0.1267
2.000 0.7419 0.01702 0.00788 -0.0962 0.7062 0.1433
2.250 0.7681 0.01478 0.00724 -0.0955 0.6920 1.0000
2.500 0.7943 0.01491 0.00705 -0.0945 0.6760 1.0000
2.750 0.8200 0.01505 0.00694 -0.0935 0.6590 1.0000
3.000 0.8455 0.01521 0.00688 -0.0925 0.6411 1.0000
3.250 0.8702 0.01542 0.00697 -0.0916 0.6211 1.0000
3.500 0.8953 0.01565 0.00705 -0.0907 0.6017 1.0000
3.750 0.9200 0.01593 0.00720 -0.0899 0.5812 1.0000
4.000 0.9445 0.01623 0.00737 -0.0890 0.5595 1.0000
4.250 0.9685 0.01656 0.00758 -0.0880 0.5362 1.0000
4.500 0.9926 0.01691 0.00781 -0.0871 0.5131 1.0000
4.750 1.0161 0.01728 0.00813 -0.0862 0.4879 1.0000
5.000 1.0396 0.01767 0.00845 -0.0854 0.4640 1.0000
5.250 1.0632 0.01805 0.00874 -0.0846 0.4420 1.0000
5.500 1.0868 0.01849 0.00917 -0.0838 0.4210 1.0000
5.750 1.1106 0.01897 0.00964 -0.0832 0.4031 1.0000
6.000 1.1342 0.01946 0.01008 -0.0825 0.3866 1.0000
6.250 1.1560 0.01987 0.01045 -0.0815 0.3652 1.0000
6.500 1.1775 0.02034 0.01087 -0.0806 0.3452 1.0000
6.750 1.1977 0.02082 0.01136 -0.0795 0.3222 1.0000
7.000 1.2174 0.02138 0.01184 -0.0785 0.3008 1.0000
7.250 1.2384 0.02199 0.01250 -0.0775 0.2846 1.0000
7.500 1.2591 0.02260 0.01321 -0.0766 0.2686 1.0000
7.750 1.2762 0.02319 0.01379 -0.0752 0.2427 1.0000
8.000 1.2944 0.02378 0.01446 -0.0740 0.2163 1.0000
8.250 1.3135 0.02439 0.01514 -0.0729 0.1762 1.0000
8.500 1.3245 0.02598 0.01615 -0.0710 0.1127 1.0000
8.750 1.3292 0.02842 0.01810 -0.0683 0.0517 1.0000
9.000 1.3374 0.03037 0.02018 -0.0659 0.0445 1.0000
9.250 1.3451 0.03220 0.02222 -0.0635 0.0411 1.0000
9.500 1.3523 0.03381 0.02408 -0.0610 0.0397 1.0000
9.750 1.3554 0.03558 0.02609 -0.0582 0.0387 1.0000
10.000 1.3558 0.03759 0.02832 -0.0555 0.0380 1.0000
10.250 1.3541 0.03986 0.03085 -0.0531 0.0375 1.0000
10.500 1.3511 0.04238 0.03355 -0.0511 0.0371 1.0000
10.750 1.3476 0.04511 0.03646 -0.0494 0.0369 1.0000
11.000 1.3445 0.04797 0.03946 -0.0479 0.0367 1.0000
11.250 1.3432 0.05078 0.04239 -0.0466 0.0364 1.0000
11.500 1.3443 0.05346 0.04514 -0.0453 0.0359 1.0000
11.750 1.3483 0.05596 0.04769 -0.0437 0.0349 1.0000
12.000 1.3592 0.05804 0.04974 -0.0417 0.0338 1.0000
12.250 1.3832 0.05961 0.05134 -0.0393 0.0336 1.0000
12.500 1.4055 0.06167 0.05361 -0.0375 0.0344 1.0000
12.750 1.4188 0.06455 0.05686 -0.0359 0.0356 1.0000
13.000 1.4230 0.06807 0.06072 -0.0347 0.0367 1.0000
13.250 1.4216 0.07207 0.06503 -0.0338 0.0378 1.0000
13.500 1.4160 0.07648 0.06974 -0.0333 0.0388 1.0000
13.750 1.4075 0.08130 0.07483 -0.0332 0.0397 1.0000
14.000 1.3978 0.08661 0.08039 -0.0335 0.0406 1.0000
14.250 1.4065 0.09134 0.08532 -0.0327 0.0425 1.0000
14.500 1.3868 0.09586 0.09010 -0.0344 0.0429 1.0000
14.750 1.3650 0.10140 0.09590 -0.0371 0.0432 1.0000
15.000 1.3422 0.10773 0.10247 -0.0406 0.0434 1.0000
15.250 1.3187 0.11482 0.10978 -0.0450 0.0436 1.0000
15.500 1.2951 0.12268 0.11784 -0.0503 0.0437 1.0000
15.750 1.2713 0.13136 0.12670 -0.0565 0.0437 1.0000
16.000 1.2470 0.14104 0.13653 -0.0636 0.0437 1.0000
16.250 1.2217 0.15207 0.14769 -0.0719 0.0436 1.0000
16.500 1.1928 0.16550 0.16117 -0.0819 0.0437 1.0000
16.750 1.1343 0.19487 0.19043 -0.1017 0.0473 1.0000
17.000 1.1336 0.20239 0.19791 -0.1052 0.0510 1.0000
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Polar data table (+)
Polar graphs
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