FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-227 (fx83w227-il) Reynolds number: 50,000 Max Cl/Cd: 6.96 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w227-il-50000-n5.txt Download as CSV file: xf-fx83w227-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-227
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3809 0.14223 0.13460 -0.0523 1.0000 0.1175
-13.750 -0.3909 0.13805 0.13045 -0.0533 0.9989 0.1192
-13.250 -0.4458 0.11550 0.10784 -0.0675 0.9906 0.1236
-13.000 -0.4084 0.11654 0.10884 -0.0684 0.9851 0.1257
-12.750 -0.4015 0.11197 0.10423 -0.0721 0.9807 0.1283
-12.500 -0.4720 0.09465 0.08682 -0.0812 0.9752 0.1313
-12.250 -0.6151 0.07319 0.06486 -0.0914 0.9666 0.1315
-12.000 -0.6548 0.06696 0.05829 -0.0930 0.9577 0.1328
-11.750 -0.6838 0.06292 0.05392 -0.0921 0.9478 0.1342
-11.500 -0.7057 0.05957 0.05017 -0.0908 0.9394 0.1360
-11.250 -0.6960 0.05817 0.04876 -0.0901 0.9312 0.1385
-11.000 -0.6749 0.05671 0.04725 -0.0912 0.9262 0.1419
-10.750 -0.6819 0.05535 0.04574 -0.0880 0.9162 0.1442
-10.500 -0.6791 0.05349 0.04359 -0.0868 0.9098 0.1477
-10.250 -0.6944 0.05227 0.04210 -0.0818 0.8991 0.1499
-10.000 -0.6659 0.05110 0.04096 -0.0831 0.8943 0.1541
-9.750 -0.6571 0.05022 0.04003 -0.0811 0.8867 0.1577
-9.500 -0.6480 0.04907 0.03869 -0.0794 0.8793 0.1619
-9.250 -0.6244 0.04771 0.03714 -0.0800 0.8749 0.1675
-9.000 -0.6205 0.04728 0.03674 -0.0768 0.8658 0.1712
-8.750 -0.6011 0.04631 0.03565 -0.0764 0.8601 0.1771
-8.500 -0.5719 0.04519 0.03440 -0.0775 0.8563 0.1844
-8.250 -0.5741 0.04495 0.03419 -0.0732 0.8463 0.1885
-8.000 -0.5529 0.04408 0.03314 -0.0728 0.8410 0.1965
-7.750 -0.5201 0.04321 0.03233 -0.0743 0.8377 0.2055
-7.500 -0.5274 0.04310 0.03217 -0.0690 0.8272 0.2107
-7.250 -0.5031 0.04237 0.03141 -0.0690 0.8223 0.2203
-7.000 -0.4744 0.04156 0.03049 -0.0697 0.8188 0.2330
-6.750 -0.4837 0.04163 0.03066 -0.0641 0.8083 0.2385
-6.500 -0.4626 0.04100 0.02996 -0.0634 0.8033 0.2519
-6.250 -0.4347 0.04024 0.02926 -0.0638 0.7998 0.2677
-6.000 -0.4473 0.04043 0.02951 -0.0577 0.7892 0.2749
-5.750 -0.4289 0.03989 0.02901 -0.0565 0.7842 0.2921
-5.500 -0.4034 0.03917 0.02837 -0.0563 0.7807 0.3140
-5.250 -0.4174 0.03947 0.02869 -0.0501 0.7700 0.3255
-5.000 -0.4002 0.03900 0.02835 -0.0485 0.7650 0.3492
-4.750 -0.3755 0.03841 0.02789 -0.0480 0.7616 0.3793
-4.500 -0.3886 0.03884 0.02841 -0.0418 0.7510 0.3955
-4.250 -0.3706 0.03858 0.02827 -0.0401 0.7459 0.4273
-4.000 -0.3445 0.03829 0.02809 -0.0394 0.7427 0.4636
-3.750 -0.3546 0.03892 0.02882 -0.0337 0.7324 0.4839
-3.500 -0.3350 0.03902 0.02900 -0.0319 0.7273 0.5153
-3.250 -0.3066 0.03901 0.02901 -0.0313 0.7240 0.5481
-3.000 -0.3134 0.03977 0.02980 -0.0261 0.7143 0.5678
-2.750 -0.2954 0.04003 0.03003 -0.0242 0.7088 0.5941
-2.500 -0.2691 0.04003 0.02996 -0.0232 0.7053 0.6212
-2.250 -0.2722 0.04085 0.03077 -0.0187 0.6963 0.6390
-2.000 -0.2570 0.04119 0.03105 -0.0164 0.6903 0.6609
-1.750 -0.2281 0.04135 0.03117 -0.0157 0.6867 0.6828
-1.500 -0.2257 0.04211 0.03191 -0.0120 0.6787 0.7005
-1.250 -0.2107 0.04267 0.03244 -0.0098 0.6722 0.7186
-1.000 -0.1813 0.04287 0.03258 -0.0093 0.6684 0.7379
-0.750 -0.1450 0.04293 0.03257 -0.0098 0.6659 0.7565
-0.500 -0.1589 0.04420 0.03387 -0.0046 0.6543 0.7710
-0.250 -0.1311 0.04438 0.03397 -0.0042 0.6503 0.7884
0.000 -0.0975 0.04432 0.03380 -0.0045 0.6476 0.8055
0.250 -0.0995 0.04579 0.03531 -0.0014 0.6367 0.8181
0.500 -0.0679 0.04609 0.03554 -0.0021 0.6323 0.8322
0.750 -0.0322 0.04608 0.03544 -0.0031 0.6295 0.8467
1.000 -0.0243 0.04767 0.03704 -0.0021 0.6196 0.8585
1.250 0.0093 0.04816 0.03747 -0.0036 0.6146 0.8704
1.500 0.0524 0.04832 0.03754 -0.0062 0.6115 0.8820
2.000 0.0979 0.05064 0.03980 -0.0082 0.5969 0.9044
2.250 0.1507 0.05097 0.04004 -0.0129 0.5936 0.9115
2.500 0.1956 0.05090 0.03989 -0.0158 0.5912 0.9219
2.750 0.2004 0.05353 0.04256 -0.0164 0.5793 0.9317
3.000 0.2414 0.05377 0.04274 -0.0193 0.5756 0.9414
3.250 0.2887 0.05371 0.04261 -0.0229 0.5731 0.9501
3.500 0.2891 0.05649 0.04544 -0.0232 0.5614 0.9620
3.750 0.3283 0.05684 0.04574 -0.0263 0.5575 0.9716
4.000 0.3741 0.05677 0.04562 -0.0298 0.5550 0.9812
4.500 0.4066 0.06025 0.04911 -0.0328 0.5396 1.0000
4.750 0.4157 0.05974 0.04852 -0.0302 0.5368 1.0000
5.000 0.3706 0.06219 0.05094 -0.0234 0.5255 1.0000
5.250 0.3763 0.06232 0.05098 -0.0208 0.5211 1.0000
5.500 0.3934 0.06214 0.05070 -0.0192 0.5184 1.0000
5.750 0.3644 0.06506 0.05357 -0.0149 0.5079 1.0000
6.000 0.3767 0.06559 0.05403 -0.0134 0.5033 1.0000
6.250 0.3982 0.06568 0.05404 -0.0126 0.5005 1.0000
6.500 0.3778 0.06871 0.05706 -0.0095 0.4908 1.0000
6.750 0.3891 0.06970 0.05800 -0.0083 0.4861 1.0000
7.000 0.4104 0.07001 0.05825 -0.0076 0.4830 1.0000
7.500 0.4067 0.07415 0.06235 -0.0044 0.4690 1.0000
7.750 0.4265 0.07475 0.06292 -0.0038 0.4656 1.0000
8.000 0.4514 0.07500 0.06312 -0.0034 0.4633 1.0000
8.250 0.4262 0.07905 0.06722 -0.0013 0.4524 1.0000
8.500 0.4441 0.07990 0.06804 -0.0007 0.4486 1.0000
8.750 0.4676 0.08034 0.06846 -0.0004 0.4460 1.0000
9.000 0.4477 0.08427 0.07242 0.0011 0.4365 1.0000
9.250 0.4621 0.08545 0.07360 0.0017 0.4319 1.0000
9.500 0.4845 0.08603 0.07417 0.0020 0.4290 1.0000
9.750 0.4743 0.08941 0.07759 0.0029 0.4215 1.0000
10.000 0.4807 0.09132 0.07951 0.0035 0.4156 1.0000
10.250 0.5009 0.09211 0.08030 0.0037 0.4121 1.0000
10.500 0.5267 0.09244 0.08064 0.0040 0.4097 1.0000
11.000 0.5176 0.09847 0.08675 0.0050 0.3956 1.0000
11.250 0.5420 0.09893 0.08723 0.0052 0.3928 1.0000
11.500 0.5238 0.10326 0.09161 0.0056 0.3839 1.0000
11.750 0.5362 0.10484 0.09323 0.0058 0.3792 1.0000
12.000 0.5586 0.10547 0.09388 0.0060 0.3759 1.0000
12.250 0.5484 0.10916 0.09763 0.0061 0.3681 1.0000
12.500 0.5565 0.11116 0.09967 0.0062 0.3626 1.0000
12.750 0.5769 0.11200 0.10055 0.0063 0.3591 1.0000
13.000 0.5741 0.11505 0.10365 0.0063 0.3523 1.0000
13.250 0.5778 0.11748 0.10613 0.0062 0.3460 1.0000
13.500 0.5968 0.11844 0.10714 0.0063 0.3423 1.0000
14.000 0.5996 0.12382 0.11263 0.0059 0.3292 1.0000
14.250 0.6186 0.12473 0.11359 0.0060 0.3253 1.0000
14.750 0.6224 0.13006 0.11904 0.0054 0.3121 1.0000
15.000 0.6420 0.13086 0.11990 0.0054 0.3082 1.0000
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