BE50 (original) (be50-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 100,000 Max Cl/Cd: 59.69 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50-il-100000.txt Download as CSV file: xf-be50-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BE50 (original)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3677 0.09510 0.09029 -0.0205 1.0000 0.0823
-8.000 -0.3729 0.09346 0.08875 -0.0227 1.0000 0.0851
-7.750 -0.3750 0.09229 0.08768 -0.0336 1.0000 0.0865
-7.500 -0.3700 0.08713 0.08258 -0.0286 1.0000 0.0880
-7.250 -0.3615 0.08385 0.07933 -0.0243 1.0000 0.0909
-7.000 -0.3558 0.08113 0.07664 -0.0247 1.0000 0.0947
-6.750 -0.3393 0.07793 0.07339 -0.0436 1.0000 0.1009
-6.500 -0.3422 0.07448 0.07008 -0.0319 1.0000 0.1033
-6.250 -0.3345 0.07200 0.06763 -0.0301 1.0000 0.1090
-6.000 -0.3154 0.06754 0.06311 -0.0400 1.0000 0.1163
-5.750 -0.3096 0.06506 0.06069 -0.0360 1.0000 0.1196
-5.500 -0.2827 0.06059 0.05608 -0.0454 1.0000 0.1305
-5.250 -0.2761 0.05824 0.05379 -0.0416 1.0000 0.1341
-5.000 -0.2499 0.05423 0.04966 -0.0478 1.0000 0.1459
-4.750 -0.2274 0.05111 0.04645 -0.0509 1.0000 0.1599
-4.500 -0.2074 0.04838 0.04366 -0.0523 1.0000 0.1746
-4.250 -0.1853 0.04564 0.04084 -0.0541 1.0000 0.1892
-4.000 -0.1639 0.04311 0.03826 -0.0552 1.0000 0.2042
-3.750 -0.0652 0.02966 0.02291 -0.0739 1.0000 0.0988
-3.500 -0.0327 0.02692 0.01977 -0.0757 1.0000 0.0968
-3.250 0.0043 0.02409 0.01632 -0.0778 1.0000 0.0911
-3.000 0.0391 0.02224 0.01386 -0.0790 1.0000 0.0885
-2.750 0.0692 0.02102 0.01240 -0.0797 1.0000 0.0893
-2.500 0.0974 0.02018 0.01143 -0.0802 1.0000 0.0922
-2.250 0.1237 0.01977 0.01090 -0.0805 1.0000 0.0991
-2.000 0.1517 0.01913 0.01029 -0.0811 1.0000 0.1051
-1.750 0.2022 0.01830 0.00955 -0.0856 0.9940 0.1211
-1.500 0.2554 0.01644 0.00882 -0.0909 0.9884 0.3479
-1.250 0.2922 0.01477 0.00868 -0.0918 0.9778 1.0000
-1.000 0.3431 0.01490 0.00844 -0.0964 0.9653 1.0000
-0.750 0.3917 0.01496 0.00824 -0.1004 0.9535 1.0000
-0.500 0.4380 0.01495 0.00806 -0.1040 0.9418 1.0000
-0.250 0.4807 0.01489 0.00787 -0.1066 0.9286 1.0000
0.000 0.5206 0.01477 0.00766 -0.1086 0.9150 1.0000
0.250 0.5583 0.01459 0.00741 -0.1099 0.9008 1.0000
0.500 0.5941 0.01437 0.00714 -0.1106 0.8859 1.0000
0.750 0.6282 0.01412 0.00684 -0.1109 0.8703 1.0000
1.000 0.6571 0.01397 0.00665 -0.1102 0.8504 1.0000
1.250 0.6873 0.01376 0.00640 -0.1096 0.8309 1.0000
1.500 0.7156 0.01363 0.00624 -0.1086 0.8089 1.0000
1.750 0.7434 0.01355 0.00607 -0.1075 0.7852 1.0000
2.000 0.7694 0.01359 0.00602 -0.1062 0.7575 1.0000
2.250 0.7950 0.01372 0.00605 -0.1048 0.7276 1.0000
2.500 0.8197 0.01393 0.00615 -0.1034 0.6940 1.0000
2.750 0.8443 0.01421 0.00629 -0.1021 0.6582 1.0000
3.000 0.8686 0.01456 0.00648 -0.1008 0.6211 1.0000
3.250 0.8930 0.01496 0.00675 -0.0997 0.5853 1.0000
3.500 0.9176 0.01542 0.00703 -0.0988 0.5533 1.0000
3.750 0.9424 0.01593 0.00740 -0.0980 0.5248 1.0000
4.000 0.9674 0.01646 0.00786 -0.0973 0.4985 1.0000
4.250 0.9924 0.01700 0.00839 -0.0967 0.4751 1.0000
4.500 1.0175 0.01752 0.00886 -0.0961 0.4543 1.0000
4.750 1.0425 0.01808 0.00941 -0.0955 0.4345 1.0000
5.000 1.0675 0.01870 0.01002 -0.0949 0.4157 1.0000
5.250 1.0926 0.01943 0.01073 -0.0944 0.3982 1.0000
5.500 1.1179 0.02027 0.01152 -0.0939 0.3815 1.0000
5.750 1.1413 0.02099 0.01236 -0.0931 0.3614 1.0000
6.000 1.1640 0.02163 0.01295 -0.0923 0.3396 1.0000
6.250 1.1840 0.02198 0.01339 -0.0910 0.3134 1.0000
6.500 1.2022 0.02204 0.01356 -0.0895 0.2829 1.0000
6.750 1.2223 0.02220 0.01393 -0.0883 0.2554 1.0000
7.000 1.2408 0.02239 0.01422 -0.0869 0.2047 1.0000
7.250 1.2426 0.02578 0.01640 -0.0836 0.0720 1.0000
7.500 1.2536 0.02801 0.01860 -0.0812 0.0580 1.0000
7.750 1.2631 0.03016 0.02081 -0.0786 0.0526 1.0000
8.000 1.2757 0.03200 0.02279 -0.0762 0.0490 1.0000
8.250 1.2880 0.03398 0.02484 -0.0741 0.0458 1.0000
8.500 1.3011 0.03684 0.02762 -0.0723 0.0428 1.0000
8.750 1.3193 0.03882 0.02985 -0.0707 0.0408 1.0000
9.000 1.3391 0.04144 0.03268 -0.0694 0.0397 1.0000
9.250 1.3575 0.04441 0.03593 -0.0680 0.0391 1.0000
9.500 1.3722 0.04771 0.03958 -0.0664 0.0389 1.0000
9.750 1.3814 0.05129 0.04356 -0.0642 0.0390 1.0000
10.000 1.3843 0.05507 0.04781 -0.0617 0.0393 1.0000
10.250 1.3813 0.05897 0.05213 -0.0590 0.0397 1.0000
10.500 1.3720 0.06272 0.05624 -0.0558 0.0401 1.0000
10.750 1.3577 0.06638 0.06020 -0.0527 0.0404 1.0000
11.000 1.3406 0.07030 0.06441 -0.0504 0.0406 1.0000
11.250 1.3219 0.07468 0.06904 -0.0490 0.0409 1.0000
11.500 1.3018 0.07958 0.07418 -0.0489 0.0412 1.0000
11.750 1.2806 0.08510 0.07993 -0.0499 0.0415 1.0000
12.000 1.2587 0.09131 0.08633 -0.0521 0.0418 1.0000
12.250 1.2372 0.09820 0.09338 -0.0552 0.0422 1.0000
12.500 1.2172 0.10566 0.10092 -0.0587 0.0427 1.0000
12.750 1.2017 0.11290 0.10831 -0.0623 0.0433 1.0000
13.000 1.1693 0.12352 0.11916 -0.0721 0.0442 1.0000
13.250 0.9819 0.11535 0.11108 -0.0499 0.0433 1.0000
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Polar data table (+)
Polar graphs
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