BE50 (original) (be50-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 50,000 Max Cl/Cd: 43.15 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50-il-50000-n5.txt Download as CSV file: xf-be50-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3737 0.10503 0.09820 -0.0193 1.0000 0.1056
-8.500 -0.3803 0.10367 0.09697 -0.0214 1.0000 0.1089
-8.250 -0.3858 0.10221 0.09564 -0.0256 1.0000 0.1098
-8.000 -0.3762 0.09747 0.09096 -0.0239 1.0000 0.1112
-7.750 -0.3672 0.09373 0.08724 -0.0226 1.0000 0.1135
-7.500 -0.3617 0.09079 0.08436 -0.0229 1.0000 0.1174
-7.250 -0.3620 0.08892 0.08259 -0.0298 1.0000 0.1234
-7.000 -0.3544 0.08497 0.07867 -0.0265 1.0000 0.1273
-6.750 -0.3472 0.08209 0.07582 -0.0270 1.0000 0.1334
-6.250 -0.3035 0.06623 0.05967 -0.0503 1.0000 0.0672
-6.000 -0.2930 0.06299 0.05643 -0.0493 1.0000 0.0659
-5.750 -0.2758 0.05885 0.05223 -0.0517 1.0000 0.0646
-5.500 -0.2509 0.05379 0.04697 -0.0570 1.0000 0.0648
-5.250 -0.2185 0.04809 0.04083 -0.0638 1.0000 0.0663
-5.000 -0.1893 0.04355 0.03591 -0.0678 1.0000 0.0661
-4.750 -0.1588 0.03941 0.03133 -0.0713 1.0000 0.0657
-4.500 -0.1273 0.03577 0.02717 -0.0742 1.0000 0.0658
-4.250 -0.0953 0.03269 0.02346 -0.0764 1.0000 0.0666
-4.000 -0.0686 0.03076 0.02131 -0.0775 1.0000 0.0704
-3.750 -0.0412 0.02917 0.01943 -0.0782 1.0000 0.0740
-3.500 -0.0115 0.02738 0.01720 -0.0790 1.0000 0.0755
-3.250 0.0170 0.02594 0.01537 -0.0794 1.0000 0.0774
-3.000 0.0447 0.02481 0.01388 -0.0796 1.0000 0.0798
-2.750 0.0717 0.02388 0.01274 -0.0797 1.0000 0.0829
-2.500 0.0984 0.02325 0.01203 -0.0799 1.0000 0.0886
-2.250 0.1255 0.02284 0.01150 -0.0802 1.0000 0.1002
-2.000 0.1657 0.02226 0.01082 -0.0830 0.9942 0.1195
-1.750 0.2091 0.02145 0.01016 -0.0864 0.9872 0.1743
-1.500 0.2508 0.02025 0.01021 -0.0900 0.9799 0.4417
-1.250 0.2796 0.01871 0.00990 -0.0893 0.9659 1.0000
-1.000 0.3248 0.01890 0.00960 -0.0928 0.9517 1.0000
-0.750 0.3679 0.01899 0.00935 -0.0957 0.9351 1.0000
-0.500 0.4087 0.01900 0.00910 -0.0979 0.9164 1.0000
-0.250 0.4480 0.01899 0.00888 -0.0998 0.8994 1.0000
0.000 0.4842 0.01899 0.00873 -0.1010 0.8835 1.0000
0.250 0.5190 0.01900 0.00862 -0.1020 0.8682 1.0000
0.500 0.5524 0.01901 0.00852 -0.1026 0.8520 1.0000
0.750 0.5835 0.01904 0.00850 -0.1027 0.8339 1.0000
1.000 0.6155 0.01903 0.00843 -0.1029 0.8159 1.0000
1.250 0.6478 0.01900 0.00834 -0.1031 0.7977 1.0000
1.500 0.6773 0.01906 0.00837 -0.1027 0.7765 1.0000
1.750 0.7075 0.01909 0.00835 -0.1024 0.7551 1.0000
2.000 0.7357 0.01920 0.00841 -0.1017 0.7313 1.0000
2.250 0.7638 0.01933 0.00851 -0.1010 0.7068 1.0000
2.500 0.7908 0.01951 0.00863 -0.1001 0.6807 1.0000
2.750 0.8165 0.01978 0.00885 -0.0991 0.6524 1.0000
3.250 0.8672 0.02044 0.00944 -0.0971 0.5934 1.0000
3.500 0.8919 0.02085 0.00980 -0.0961 0.5635 1.0000
3.750 0.9166 0.02130 0.01019 -0.0952 0.5356 1.0000
4.000 0.9411 0.02182 0.01073 -0.0943 0.5090 1.0000
4.250 0.9656 0.02238 0.01131 -0.0936 0.4839 1.0000
4.500 0.9901 0.02296 0.01190 -0.0929 0.4612 1.0000
4.750 1.0146 0.02357 0.01257 -0.0922 0.4402 1.0000
5.000 1.0391 0.02420 0.01327 -0.0915 0.4218 1.0000
5.250 1.0637 0.02490 0.01402 -0.0909 0.4044 1.0000
5.500 1.0882 0.02567 0.01489 -0.0903 0.3877 1.0000
5.750 1.1126 0.02649 0.01585 -0.0897 0.3718 1.0000
6.000 1.1368 0.02738 0.01688 -0.0890 0.3566 1.0000
6.250 1.1607 0.02830 0.01806 -0.0884 0.3417 1.0000
6.500 1.1842 0.02927 0.01926 -0.0876 0.3270 1.0000
6.750 1.2048 0.03012 0.02031 -0.0865 0.3081 1.0000
7.000 1.2185 0.03064 0.02099 -0.0844 0.2782 1.0000
7.250 1.2262 0.03104 0.02144 -0.0819 0.2337 1.0000
7.500 1.2352 0.03203 0.02230 -0.0798 0.1775 1.0000
7.750 1.2420 0.03415 0.02399 -0.0778 0.1001 1.0000
8.000 1.2438 0.03733 0.02676 -0.0754 0.0615 1.0000
8.250 1.2475 0.04008 0.02953 -0.0730 0.0512 1.0000
8.500 1.2486 0.04280 0.03232 -0.0705 0.0465 1.0000
8.750 1.2498 0.04521 0.03497 -0.0678 0.0430 1.0000
9.000 1.2487 0.04777 0.03772 -0.0654 0.0401 1.0000
9.250 1.2456 0.05061 0.04071 -0.0633 0.0377 1.0000
9.500 1.2399 0.05387 0.04410 -0.0616 0.0359 1.0000
9.750 1.2377 0.05701 0.04742 -0.0602 0.0345 1.0000
10.000 1.2382 0.06009 0.05078 -0.0590 0.0334 1.0000
10.250 1.2389 0.06332 0.05427 -0.0579 0.0325 1.0000
10.500 1.2395 0.06674 0.05796 -0.0570 0.0318 1.0000
10.750 1.2390 0.07042 0.06191 -0.0564 0.0311 1.0000
11.000 1.2367 0.07447 0.06623 -0.0562 0.0306 1.0000
11.250 1.2318 0.07897 0.07102 -0.0566 0.0303 1.0000
11.500 1.2240 0.08400 0.07631 -0.0576 0.0299 1.0000
11.750 1.2138 0.08960 0.08216 -0.0594 0.0298 1.0000
12.000 1.2013 0.09580 0.08861 -0.0619 0.0297 1.0000
12.250 1.1871 0.10267 0.09572 -0.0652 0.0297 1.0000
12.500 1.1713 0.11028 0.10356 -0.0693 0.0299 1.0000
12.750 1.1542 0.11871 0.11219 -0.0741 0.0303 1.0000
13.000 1.1364 0.12796 0.12163 -0.0797 0.0308 1.0000
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Polar data table (+)
Polar graphs
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