FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 50,000 Max Cl/Cd: 24.33 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w127-il-50000-n5.txt Download as CSV file: xf-fx84w127-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-127
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3351 0.11037 0.10342 -0.0526 1.0000 0.0651
-10.250 -0.3352 0.10695 0.10007 -0.0534 1.0000 0.0650
-10.000 -0.3367 0.10378 0.09699 -0.0536 1.0000 0.0649
-9.750 -0.3400 0.10107 0.09437 -0.0531 1.0000 0.0646
-9.500 -0.3478 0.09875 0.09216 -0.0518 1.0000 0.0642
-9.250 -0.3598 0.09677 0.09030 -0.0499 1.0000 0.0638
-9.000 -0.3745 0.09507 0.08871 -0.0476 1.0000 0.0634
-8.750 -0.3915 0.09340 0.08715 -0.0453 1.0000 0.0629
-8.500 -0.3929 0.08916 0.08295 -0.0486 0.9934 0.0623
-8.250 -0.3899 0.08335 0.07713 -0.0554 0.9832 0.0616
-8.000 -0.3891 0.07697 0.07070 -0.0630 0.9719 0.0609
-7.750 -0.3886 0.07070 0.06430 -0.0692 0.9607 0.0607
-7.500 -0.3881 0.06510 0.05848 -0.0737 0.9502 0.0609
-7.250 -0.3836 0.05956 0.05260 -0.0779 0.9413 0.0619
-7.000 -0.3785 0.05458 0.04715 -0.0803 0.9319 0.0632
-6.750 -0.3699 0.05025 0.04225 -0.0814 0.9231 0.0643
-6.500 -0.3524 0.04615 0.03754 -0.0829 0.9163 0.0654
-6.250 -0.3326 0.04410 0.03535 -0.0832 0.9093 0.0676
-6.000 -0.3096 0.04222 0.03322 -0.0838 0.9027 0.0714
-5.750 -0.2854 0.03960 0.03000 -0.0845 0.8969 0.0752
-5.500 -0.2656 0.03741 0.02723 -0.0839 0.8892 0.0781
-5.250 -0.2354 0.03603 0.02580 -0.0851 0.8845 0.0835
-5.000 -0.2154 0.03476 0.02418 -0.0841 0.8768 0.0887
-4.750 -0.1869 0.03337 0.02254 -0.0844 0.8714 0.0944
-4.500 -0.1586 0.03238 0.02134 -0.0847 0.8659 0.1030
-4.250 -0.1361 0.03152 0.02039 -0.0839 0.8587 0.1100
-4.000 -0.1044 0.03064 0.01935 -0.0845 0.8542 0.1224
-3.750 -0.0829 0.03009 0.01870 -0.0835 0.8470 0.1339
-3.500 -0.0556 0.02947 0.01802 -0.0835 0.8411 0.1510
-3.250 -0.0230 0.02869 0.01731 -0.0845 0.8372 0.1749
-3.000 -0.0077 0.02838 0.01702 -0.0827 0.8284 0.1994
-2.750 0.0200 0.02765 0.01650 -0.0829 0.8235 0.2463
-2.500 0.0375 0.02707 0.01631 -0.0817 0.8162 0.3150
-2.250 0.0554 0.02616 0.01623 -0.0801 0.8101 0.4673
-2.000 0.0748 0.02559 0.01650 -0.0763 0.8061 0.6915
-1.750 0.0867 0.02589 0.01693 -0.0722 0.7975 0.8046
-1.500 0.1307 0.02600 0.01690 -0.0733 0.7936 0.9021
-1.250 0.2283 0.02591 0.01639 -0.0854 0.7925 0.9755
-1.000 0.2852 0.02588 0.01606 -0.0915 0.7881 1.0000
-0.750 0.2921 0.02621 0.01624 -0.0887 0.7792 1.0000
-0.500 0.3105 0.02634 0.01619 -0.0874 0.7732 1.0000
-0.250 0.3163 0.02679 0.01651 -0.0843 0.7641 1.0000
0.000 0.3425 0.02683 0.01636 -0.0841 0.7597 1.0000
0.250 0.3453 0.02747 0.01688 -0.0807 0.7495 1.0000
0.500 0.3723 0.02757 0.01682 -0.0805 0.7450 1.0000
0.750 0.3798 0.02823 0.01738 -0.0779 0.7355 1.0000
1.000 0.4069 0.02838 0.01740 -0.0778 0.7306 1.0000
1.250 0.4188 0.02903 0.01796 -0.0758 0.7219 1.0000
1.500 0.4444 0.02926 0.01809 -0.0755 0.7163 1.0000
2.000 0.4836 0.03021 0.01891 -0.0736 0.7021 1.0000
2.250 0.5158 0.03024 0.01886 -0.0740 0.6984 1.0000
2.500 0.5236 0.03123 0.01982 -0.0718 0.6880 1.0000
2.750 0.5550 0.03129 0.01984 -0.0721 0.6839 1.0000
3.000 0.5641 0.03231 0.02085 -0.0702 0.6740 1.0000
3.250 0.5939 0.03245 0.02097 -0.0704 0.6694 1.0000
3.500 0.6047 0.03346 0.02199 -0.0687 0.6600 1.0000
3.750 0.6329 0.03367 0.02221 -0.0686 0.6549 1.0000
4.000 0.6455 0.03464 0.02320 -0.0672 0.6459 1.0000
4.250 0.6718 0.03495 0.02353 -0.0669 0.6402 1.0000
4.750 0.7103 0.03624 0.02491 -0.0652 0.6253 1.0000
5.250 0.7480 0.03756 0.02633 -0.0633 0.6100 1.0000
5.750 0.7856 0.03892 0.02786 -0.0614 0.5946 1.0000
6.250 0.8238 0.04026 0.02937 -0.0596 0.5789 1.0000
6.750 0.8633 0.04147 0.03082 -0.0579 0.5631 1.0000
7.000 0.8680 0.04315 0.03259 -0.0562 0.5512 1.0000
7.250 0.9062 0.04232 0.03192 -0.0562 0.5471 1.0000
7.500 0.9095 0.04405 0.03377 -0.0544 0.5344 1.0000
8.000 0.9544 0.04454 0.03457 -0.0526 0.5177 1.0000
8.250 0.9595 0.04618 0.03634 -0.0510 0.5050 1.0000
8.750 1.0092 0.04596 0.03651 -0.0490 0.4873 1.0000
9.000 1.0172 0.04720 0.03790 -0.0475 0.4741 1.0000
9.250 1.0315 0.04773 0.03861 -0.0459 0.4608 1.0000
9.500 1.0526 0.04731 0.03839 -0.0443 0.4466 1.0000
9.750 1.0794 0.04588 0.03713 -0.0423 0.4294 1.0000
10.000 1.0984 0.04514 0.03651 -0.0402 0.4084 1.0000
10.250 1.1030 0.04614 0.03762 -0.0382 0.3855 1.0000
10.500 1.1117 0.04680 0.03837 -0.0364 0.3607 1.0000
10.750 1.1196 0.04763 0.03923 -0.0346 0.3323 1.0000
11.000 1.1233 0.04906 0.04064 -0.0331 0.3008 1.0000
11.250 1.1258 0.05064 0.04206 -0.0314 0.2649 1.0000
11.500 1.1232 0.05303 0.04425 -0.0301 0.2288 1.0000
11.750 1.1172 0.05600 0.04697 -0.0291 0.1962 1.0000
12.000 1.1100 0.05937 0.05012 -0.0283 0.1693 1.0000
12.250 1.1028 0.06293 0.05346 -0.0279 0.1484 1.0000
12.500 1.0979 0.06647 0.05690 -0.0276 0.1314 1.0000
12.750 1.0947 0.06990 0.06022 -0.0274 0.1185 1.0000
13.000 1.0932 0.07319 0.06344 -0.0273 0.1079 1.0000
13.250 1.0951 0.07620 0.06649 -0.0271 0.0983 1.0000
13.500 1.0984 0.07902 0.06931 -0.0268 0.0912 1.0000
13.750 1.1026 0.08180 0.07212 -0.0267 0.0844 1.0000
14.000 1.1096 0.08428 0.07469 -0.0263 0.0788 1.0000
14.250 1.1171 0.08678 0.07732 -0.0260 0.0737 1.0000
14.500 1.1267 0.08889 0.07939 -0.0255 0.0694 1.0000
14.750 1.1331 0.09191 0.08276 -0.0256 0.0656 1.0000
15.000 1.1410 0.09465 0.08568 -0.0255 0.0625 1.0000
15.250 1.1539 0.09649 0.08750 -0.0250 0.0593 1.0000
15.500 1.1536 0.10064 0.09195 -0.0258 0.0572 1.0000
15.750 1.1482 0.10564 0.09728 -0.0274 0.0556 1.0000
16.000 1.1410 0.11105 0.10297 -0.0294 0.0543 1.0000
16.250 1.1314 0.11703 0.10922 -0.0319 0.0534 1.0000
16.500 1.1178 0.12397 0.11641 -0.0353 0.0529 1.0000
16.750 1.0988 0.13240 0.12509 -0.0400 0.0527 1.0000
17.000 1.0702 0.14384 0.13677 -0.0470 0.0531 1.0000
17.250 1.0313 0.15982 0.15291 -0.0571 0.0542 1.0000
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