BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 50,000 Max Cl/Cd: 43.02 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50sm-il-50000-n5.txt Download as CSV file: xf-be50sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BE50 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3626 0.09643 0.08975 -0.0219 1.0000 0.1008
-7.000 -0.3599 0.09367 0.08708 -0.0230 1.0000 0.1027
-6.750 -0.3595 0.09137 0.08488 -0.0265 1.0000 0.1063
-6.250 -0.3416 0.08109 0.07461 -0.0380 1.0000 0.0659
-6.000 -0.3350 0.07784 0.07141 -0.0359 1.0000 0.0646
-5.750 -0.3261 0.07432 0.06792 -0.0370 1.0000 0.0634
-5.500 -0.3150 0.07056 0.06418 -0.0392 1.0000 0.0619
-5.000 -0.2641 0.05742 0.05059 -0.0562 1.0000 0.0530
-4.750 -0.2462 0.05359 0.04665 -0.0578 1.0000 0.0524
-4.500 -0.2225 0.04921 0.04209 -0.0611 1.0000 0.0518
-4.250 -0.1939 0.04453 0.03706 -0.0653 1.0000 0.0516
-4.000 -0.1597 0.03967 0.03161 -0.0700 1.0000 0.0524
-3.750 -0.1342 0.03698 0.02874 -0.0717 1.0000 0.0559
-3.500 -0.1048 0.03427 0.02565 -0.0736 1.0000 0.0589
-3.250 -0.0715 0.03118 0.02197 -0.0758 1.0000 0.0608
-3.000 -0.0385 0.02868 0.01874 -0.0773 1.0000 0.0648
-2.750 -0.0107 0.02720 0.01706 -0.0780 1.0000 0.0714
-2.500 0.0184 0.02568 0.01513 -0.0784 1.0000 0.0768
-2.250 0.0463 0.02454 0.01379 -0.0787 1.0000 0.0848
-2.000 0.0740 0.02368 0.01274 -0.0789 1.0000 0.0969
-1.750 0.1026 0.02294 0.01180 -0.0792 1.0000 0.1112
-1.500 0.1310 0.02240 0.01116 -0.0797 1.0000 0.1350
-1.250 0.1599 0.02185 0.01071 -0.0804 1.0000 0.1722
-1.000 0.2037 0.02098 0.01027 -0.0842 0.9938 0.2701
-0.750 0.2457 0.02001 0.01022 -0.0873 0.9852 0.5179
-0.500 0.2779 0.01886 0.00987 -0.0874 0.9701 1.0000
-0.250 0.3231 0.01905 0.00963 -0.0908 0.9559 1.0000
0.000 0.3652 0.01917 0.00943 -0.0936 0.9405 1.0000
0.250 0.4061 0.01927 0.00928 -0.0960 0.9254 1.0000
0.500 0.4459 0.01933 0.00916 -0.0981 0.9103 1.0000
0.750 0.4831 0.01936 0.00904 -0.0996 0.8944 1.0000
1.000 0.5186 0.01935 0.00893 -0.1006 0.8778 1.0000
1.250 0.5535 0.01932 0.00881 -0.1014 0.8607 1.0000
1.500 0.5881 0.01925 0.00867 -0.1019 0.8434 1.0000
1.750 0.6179 0.01926 0.00864 -0.1017 0.8224 1.0000
2.000 0.6498 0.01920 0.00853 -0.1016 0.8022 1.0000
2.250 0.6790 0.01921 0.00853 -0.1011 0.7789 1.0000
2.500 0.7087 0.01921 0.00848 -0.1005 0.7552 1.0000
2.750 0.7378 0.01924 0.00845 -0.0998 0.7298 1.0000
3.000 0.7652 0.01934 0.00850 -0.0989 0.7019 1.0000
3.250 0.7922 0.01951 0.00863 -0.0980 0.6728 1.0000
3.500 0.8180 0.01975 0.00880 -0.0969 0.6423 1.0000
3.750 0.8438 0.02007 0.00903 -0.0959 0.6116 1.0000
4.000 0.8691 0.02045 0.00933 -0.0949 0.5814 1.0000
4.250 0.8942 0.02089 0.00975 -0.0940 0.5525 1.0000
4.500 0.9191 0.02140 0.01018 -0.0931 0.5255 1.0000
4.750 0.9439 0.02194 0.01066 -0.0923 0.5008 1.0000
5.000 0.9686 0.02253 0.01125 -0.0915 0.4773 1.0000
5.250 0.9934 0.02316 0.01186 -0.0908 0.4562 1.0000
5.500 1.0182 0.02382 0.01262 -0.0902 0.4362 1.0000
5.750 1.0429 0.02451 0.01334 -0.0895 0.4181 1.0000
6.000 1.0676 0.02524 0.01412 -0.0888 0.4012 1.0000
6.250 1.0918 0.02601 0.01501 -0.0882 0.3843 1.0000
6.500 1.1159 0.02681 0.01600 -0.0875 0.3683 1.0000
6.750 1.1395 0.02764 0.01698 -0.0867 0.3526 1.0000
7.000 1.1627 0.02850 0.01801 -0.0859 0.3372 1.0000
7.250 1.1853 0.02937 0.01906 -0.0850 0.3214 1.0000
7.500 1.2068 0.03023 0.02010 -0.0839 0.3049 1.0000
7.750 1.2261 0.03104 0.02115 -0.0826 0.2858 1.0000
8.000 1.2409 0.03166 0.02190 -0.0807 0.2605 1.0000
8.250 1.2522 0.03233 0.02272 -0.0785 0.2292 1.0000
8.500 1.2633 0.03322 0.02375 -0.0765 0.1947 1.0000
8.750 1.2727 0.03453 0.02505 -0.0744 0.1551 1.0000
9.000 1.2782 0.03659 0.02691 -0.0721 0.1148 1.0000
9.250 1.2807 0.03921 0.02931 -0.0697 0.0884 1.0000
9.500 1.2820 0.04189 0.03194 -0.0672 0.0751 1.0000
9.750 1.2824 0.04445 0.03464 -0.0645 0.0663 1.0000
10.000 1.2793 0.04714 0.03733 -0.0619 0.0607 1.0000
10.250 1.2796 0.04978 0.04022 -0.0597 0.0555 1.0000
10.500 1.2778 0.05265 0.04322 -0.0578 0.0524 1.0000
10.750 1.2751 0.05578 0.04640 -0.0560 0.0502 1.0000
11.000 1.2773 0.05882 0.04975 -0.0545 0.0478 1.0000
11.250 1.2770 0.06212 0.05334 -0.0533 0.0453 1.0000
11.500 1.2741 0.06564 0.05708 -0.0526 0.0432 1.0000
11.750 1.2699 0.06934 0.06091 -0.0523 0.0413 1.0000
12.000 1.2666 0.07315 0.06478 -0.0520 0.0397 1.0000
12.250 1.2615 0.07757 0.06944 -0.0521 0.0388 1.0000
12.500 1.2532 0.08259 0.07479 -0.0530 0.0383 1.0000
12.750 1.2422 0.08819 0.08069 -0.0547 0.0379 1.0000
13.000 1.2286 0.09443 0.08720 -0.0571 0.0378 1.0000
13.250 1.2133 0.10131 0.09433 -0.0604 0.0377 1.0000
13.500 1.1968 0.10882 0.10206 -0.0645 0.0378 1.0000
13.750 1.1792 0.11703 0.11047 -0.0692 0.0379 1.0000
14.000 1.1613 0.12586 0.11946 -0.0745 0.0382 1.0000
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Polar data table (+)
Polar graphs
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