GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 500,000 Max Cl/Cd: 88.39 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe383-il-500000.txt Download as CSV file: xf-goe383-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.0985 0.11419 0.11105 -0.0663 0.7750 0.0499
-12.500 -0.6887 0.03824 0.03333 -0.1047 0.8654 0.0398
-12.250 -0.6886 0.03635 0.03119 -0.1025 0.8478 0.0397
-12.000 -0.6823 0.03460 0.02921 -0.1007 0.8307 0.0398
-11.750 -0.6723 0.03300 0.02739 -0.0992 0.8143 0.0399
-11.500 -0.6590 0.03159 0.02577 -0.0980 0.7983 0.0400
-11.250 -0.6435 0.03030 0.02431 -0.0969 0.7828 0.0401
-11.000 -0.6256 0.02916 0.02304 -0.0960 0.7687 0.0403
-10.750 -0.6066 0.02816 0.02187 -0.0952 0.7559 0.0405
-10.500 -0.5865 0.02717 0.02078 -0.0944 0.7441 0.0407
-10.250 -0.5659 0.02633 0.01979 -0.0937 0.7342 0.0409
-10.000 -0.5443 0.02551 0.01887 -0.0931 0.7254 0.0413
-9.750 -0.5227 0.02472 0.01793 -0.0924 0.7175 0.0417
-9.500 -0.5004 0.02390 0.01698 -0.0918 0.7108 0.0420
-9.250 -0.4773 0.02304 0.01600 -0.0913 0.7044 0.0422
-9.000 -0.4538 0.02227 0.01509 -0.0908 0.6980 0.0425
-8.750 -0.4299 0.02159 0.01426 -0.0902 0.6915 0.0428
-8.500 -0.4051 0.02091 0.01350 -0.0898 0.6860 0.0430
-8.250 -0.3801 0.02032 0.01280 -0.0894 0.6802 0.0433
-8.000 -0.3550 0.01983 0.01219 -0.0890 0.6747 0.0436
-7.750 -0.3295 0.01931 0.01156 -0.0886 0.6694 0.0439
-7.500 -0.3038 0.01840 0.01069 -0.0884 0.6652 0.0443
-7.250 -0.2780 0.01782 0.01012 -0.0882 0.6610 0.0448
-7.000 -0.2521 0.01736 0.00965 -0.0879 0.6569 0.0453
-6.750 -0.2262 0.01698 0.00922 -0.0875 0.6529 0.0458
-6.500 -0.2002 0.01664 0.00883 -0.0872 0.6488 0.0464
-6.250 -0.1737 0.01627 0.00845 -0.0870 0.6461 0.0471
-6.000 -0.1471 0.01595 0.00811 -0.0868 0.6429 0.0478
-5.750 -0.1201 0.01570 0.00781 -0.0865 0.6394 0.0485
-5.500 -0.0953 0.01515 0.00727 -0.0861 0.6359 0.0493
-5.250 -0.0696 0.01480 0.00692 -0.0857 0.6322 0.0501
-5.000 -0.0433 0.01457 0.00665 -0.0854 0.6282 0.0510
-4.750 -0.0165 0.01430 0.00638 -0.0852 0.6254 0.0520
-4.500 0.0105 0.01405 0.00613 -0.0850 0.6225 0.0531
-4.250 0.0367 0.01373 0.00581 -0.0847 0.6192 0.0543
-4.000 0.0631 0.01343 0.00554 -0.0844 0.6158 0.0559
-3.750 0.0903 0.01323 0.00531 -0.0842 0.6123 0.0577
-3.500 0.1173 0.01305 0.00509 -0.0840 0.6085 0.0600
-3.250 0.1444 0.01286 0.00491 -0.0839 0.6048 0.0633
-3.000 0.1714 0.01260 0.00470 -0.0837 0.6015 0.0679
-2.750 0.1982 0.01232 0.00450 -0.0834 0.5979 0.0789
-2.500 0.2234 0.01187 0.00434 -0.0831 0.5942 0.1409
-2.250 0.2497 0.01159 0.00421 -0.0829 0.5905 0.1820
-2.000 0.2757 0.01133 0.00415 -0.0827 0.5864 0.2441
-1.750 0.3024 0.01111 0.00412 -0.0825 0.5828 0.2960
-1.500 0.3292 0.01089 0.00406 -0.0824 0.5788 0.3373
-1.250 0.3557 0.01066 0.00400 -0.0822 0.5743 0.3841
-1.000 0.3812 0.01038 0.00394 -0.0818 0.5698 0.4542
-0.750 0.4065 0.01017 0.00393 -0.0813 0.5649 0.5330
-0.500 0.4314 0.00991 0.00398 -0.0807 0.5607 0.6088
-0.250 0.4575 0.00978 0.00402 -0.0802 0.5557 0.6649
0.000 0.4841 0.00972 0.00403 -0.0798 0.5505 0.7019
0.250 0.5106 0.00972 0.00406 -0.0794 0.5451 0.7338
0.500 0.5368 0.00966 0.00411 -0.0789 0.5395 0.7673
0.750 0.5629 0.00962 0.00415 -0.0783 0.5330 0.7951
1.000 0.5889 0.00965 0.00416 -0.0778 0.5266 0.8163
1.250 0.6152 0.00965 0.00424 -0.0773 0.5201 0.8374
1.500 0.6409 0.00968 0.00429 -0.0767 0.5128 0.8582
1.750 0.6659 0.00977 0.00435 -0.0760 0.5060 0.8781
2.000 0.6913 0.00981 0.00446 -0.0753 0.4984 0.8998
2.250 0.7158 0.00994 0.00455 -0.0744 0.4910 0.9227
2.500 0.7431 0.01008 0.00468 -0.0741 0.4842 0.9415
2.750 0.7742 0.01024 0.00481 -0.0748 0.4769 0.9554
3.000 0.8070 0.01048 0.00495 -0.0759 0.4694 0.9676
3.250 0.8425 0.01066 0.00511 -0.0776 0.4614 0.9783
3.500 0.8843 0.01094 0.00528 -0.0807 0.4530 0.9830
3.750 0.9257 0.01115 0.00546 -0.0837 0.4467 0.9884
4.000 0.9659 0.01137 0.00564 -0.0866 0.4407 0.9933
4.250 1.0085 0.01166 0.00583 -0.0900 0.4350 0.9975
4.500 1.0414 0.01184 0.00600 -0.0914 0.4305 1.0000
4.750 1.0546 0.01194 0.00609 -0.0889 0.4265 1.0000
5.000 1.0680 0.01209 0.00621 -0.0863 0.4224 1.0000
5.250 1.0818 0.01229 0.00636 -0.0838 0.4183 1.0000
5.500 1.0977 0.01251 0.00654 -0.0817 0.4145 1.0000
5.750 1.1151 0.01265 0.00670 -0.0799 0.4113 1.0000
6.000 1.1332 0.01282 0.00688 -0.0782 0.4077 1.0000
6.250 1.1500 0.01304 0.00708 -0.0764 0.4038 1.0000
6.500 1.1668 0.01332 0.00731 -0.0746 0.3999 1.0000
6.750 1.1861 0.01361 0.00757 -0.0733 0.3961 1.0000
7.000 1.2055 0.01382 0.00782 -0.0720 0.3929 1.0000
7.250 1.2254 0.01407 0.00810 -0.0709 0.3894 1.0000
7.500 1.2449 0.01437 0.00839 -0.0698 0.3857 1.0000
7.750 1.2642 0.01474 0.00872 -0.0687 0.3818 1.0000
8.000 1.2842 0.01510 0.00908 -0.0678 0.3780 1.0000
8.250 1.3035 0.01540 0.00944 -0.0668 0.3741 1.0000
8.500 1.3221 0.01576 0.00982 -0.0657 0.3696 1.0000
8.750 1.3394 0.01622 0.01024 -0.0645 0.3649 1.0000
9.000 1.3571 0.01670 0.01072 -0.0634 0.3603 1.0000
9.250 1.3756 0.01711 0.01120 -0.0625 0.3559 1.0000
9.500 1.3929 0.01761 0.01171 -0.0615 0.3511 1.0000
9.750 1.4083 0.01823 0.01231 -0.0603 0.3464 1.0000
10.000 1.4252 0.01881 0.01293 -0.0594 0.3419 1.0000
10.250 1.4421 0.01940 0.01356 -0.0585 0.3366 1.0000
10.500 1.4553 0.02020 0.01435 -0.0573 0.3308 1.0000
10.750 1.4692 0.02101 0.01519 -0.0562 0.3248 1.0000
11.000 1.4823 0.02190 0.01610 -0.0552 0.3174 1.0000
11.250 1.4915 0.02307 0.01724 -0.0539 0.3102 1.0000
11.500 1.5036 0.02411 0.01833 -0.0529 0.3020 1.0000
11.750 1.5106 0.02553 0.01972 -0.0516 0.2942 1.0000
12.000 1.5203 0.02682 0.02104 -0.0507 0.2860 1.0000
12.250 1.5253 0.02848 0.02268 -0.0494 0.2787 1.0000
12.500 1.5339 0.02993 0.02415 -0.0485 0.2714 1.0000
12.750 1.5365 0.03189 0.02608 -0.0473 0.2647 1.0000
13.000 1.5453 0.03342 0.02766 -0.0466 0.2585 1.0000
13.250 1.5484 0.03542 0.02966 -0.0456 0.2525 1.0000
13.500 1.5541 0.03723 0.03149 -0.0448 0.2472 1.0000
13.750 1.5593 0.03914 0.03343 -0.0441 0.2418 1.0000
14.000 1.5603 0.04143 0.03571 -0.0432 0.2366 1.0000
14.250 1.5667 0.04329 0.03761 -0.0426 0.2319 1.0000
14.500 1.5702 0.04542 0.03977 -0.0420 0.2269 1.0000
14.750 1.5707 0.04783 0.04217 -0.0413 0.2223 1.0000
15.000 1.5761 0.04985 0.04425 -0.0408 0.2184 1.0000
15.250 1.5810 0.05193 0.04638 -0.0404 0.2143 1.0000
15.500 1.5814 0.05445 0.04891 -0.0399 0.2101 1.0000
15.750 1.5832 0.05684 0.05133 -0.0395 0.2063 1.0000
16.000 1.5882 0.05899 0.05355 -0.0392 0.2023 1.0000
16.250 1.5887 0.06161 0.05621 -0.0389 0.1982 1.0000
16.500 1.5865 0.06450 0.05910 -0.0385 0.1942 1.0000
16.750 1.5909 0.06679 0.06148 -0.0384 0.1904 1.0000
17.000 1.5916 0.06947 0.06420 -0.0383 0.1859 1.0000
17.250 1.5849 0.07300 0.06774 -0.0381 0.1811 1.0000
17.500 1.5875 0.07558 0.07040 -0.0382 0.1760 1.0000
17.750 1.5804 0.07927 0.07412 -0.0382 0.1704 1.0000
18.000 1.5763 0.08265 0.07755 -0.0383 0.1640 1.0000
18.250 1.5652 0.08692 0.08183 -0.0386 0.1567 1.0000
18.500 1.5534 0.09137 0.08630 -0.0389 0.1468 1.0000
18.750 1.5343 0.09676 0.09168 -0.0395 0.1333 1.0000
19.000 1.5023 0.10390 0.09874 -0.0404 0.1124 1.0000
19.250 1.4611 0.11244 0.10718 -0.0418 0.0915 1.0000
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