BE50 (original) (be50-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: BE50 (original) (be50-il) Reynolds number: 200,000 Max Cl/Cd: 79.79 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50-il-200000.txt Download as CSV file: xf-be50-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3675 0.08762 0.08425 -0.0216 1.0000 0.0409
-7.750 -0.3681 0.08507 0.08176 -0.0221 1.0000 0.0424
-7.500 -0.3670 0.08229 0.07904 -0.0247 1.0000 0.0444
-7.250 -0.3572 0.07887 0.07564 -0.0357 1.0000 0.0462
-7.000 -0.3467 0.07357 0.07034 -0.0422 1.0000 0.0467
-6.750 -0.3522 0.07075 0.06759 -0.0350 1.0000 0.0482
-6.500 -0.3463 0.06865 0.06552 -0.0328 1.0000 0.0497
-6.250 -0.3366 0.06589 0.06276 -0.0337 1.0000 0.0516
-6.000 -0.3217 0.06231 0.05917 -0.0372 1.0000 0.0548
-5.750 -0.2792 0.05298 0.04953 -0.0543 1.0000 0.0603
-5.500 -0.2723 0.05132 0.04797 -0.0514 1.0000 0.0617
-5.250 -0.2589 0.04941 0.04606 -0.0508 1.0000 0.0645
-5.000 -0.2184 0.04291 0.03915 -0.0606 1.0000 0.0746
-4.750 -0.2019 0.04130 0.03761 -0.0599 0.9995 0.0774
-4.500 -0.1489 0.03611 0.03199 -0.0690 0.9964 0.0894
-4.250 -0.1004 0.03270 0.02820 -0.0754 0.9931 0.1027
-4.000 -0.0575 0.03027 0.02562 -0.0799 0.9883 0.1172
-3.750 0.0052 0.02020 0.01382 -0.0855 0.9894 0.0567
-3.500 0.0508 0.01808 0.01127 -0.0889 0.9860 0.0559
-3.250 0.0963 0.01696 0.00985 -0.0923 0.9825 0.0580
-3.000 0.1369 0.01575 0.00845 -0.0946 0.9763 0.0584
-2.750 0.1808 0.01458 0.00718 -0.0977 0.9721 0.0599
-2.500 0.2238 0.01358 0.00623 -0.1007 0.9672 0.0641
-2.250 0.2652 0.01303 0.00568 -0.1033 0.9600 0.0719
-2.000 0.3120 0.01219 0.00493 -0.1070 0.9560 0.0913
-1.750 0.3497 0.01099 0.00459 -0.1093 0.9467 0.3035
-1.500 0.3866 0.01035 0.00450 -0.1110 0.9380 0.4941
-1.250 0.4175 0.00951 0.00429 -0.1111 0.9273 0.6736
-1.000 0.4423 0.00875 0.00395 -0.1091 0.9127 1.0000
-0.750 0.4709 0.00866 0.00372 -0.1088 0.8962 1.0000
-0.500 0.4993 0.00859 0.00352 -0.1083 0.8784 1.0000
-0.250 0.5276 0.00852 0.00333 -0.1079 0.8601 1.0000
0.000 0.5555 0.00849 0.00317 -0.1073 0.8405 1.0000
0.250 0.5826 0.00853 0.00307 -0.1066 0.8187 1.0000
0.500 0.6095 0.00861 0.00300 -0.1059 0.7967 1.0000
0.750 0.6362 0.00873 0.00298 -0.1053 0.7736 1.0000
1.000 0.6627 0.00889 0.00300 -0.1046 0.7498 1.0000
1.250 0.6890 0.00909 0.00305 -0.1039 0.7260 1.0000
1.500 0.7152 0.00929 0.00313 -0.1033 0.7009 1.0000
1.750 0.7414 0.00950 0.00322 -0.1027 0.6751 1.0000
2.000 0.7674 0.00973 0.00333 -0.1021 0.6479 1.0000
2.250 0.7932 0.00998 0.00347 -0.1015 0.6181 1.0000
2.500 0.8186 0.01026 0.00361 -0.1008 0.5845 1.0000
2.750 0.8437 0.01058 0.00377 -0.1002 0.5466 1.0000
3.000 0.8684 0.01100 0.00398 -0.0995 0.5096 1.0000
3.250 0.8937 0.01138 0.00426 -0.0990 0.4739 1.0000
3.500 0.9189 0.01177 0.00451 -0.0985 0.4432 1.0000
3.750 0.9440 0.01221 0.00481 -0.0980 0.4195 1.0000
4.000 0.9692 0.01268 0.00518 -0.0976 0.4005 1.0000
4.250 0.9944 0.01318 0.00562 -0.0972 0.3839 1.0000
4.500 1.0197 0.01368 0.00607 -0.0968 0.3689 1.0000
4.750 1.0448 0.01419 0.00653 -0.0964 0.3530 1.0000
5.000 1.0696 0.01458 0.00694 -0.0959 0.3332 1.0000
5.250 1.0941 0.01495 0.00734 -0.0954 0.3133 1.0000
5.500 1.1184 0.01534 0.00771 -0.0949 0.2951 1.0000
5.750 1.1432 0.01556 0.00801 -0.0945 0.2714 1.0000
6.000 1.1677 0.01585 0.00832 -0.0940 0.2456 1.0000
6.250 1.1911 0.01630 0.00871 -0.0935 0.2116 1.0000
6.500 1.2117 0.01721 0.00934 -0.0926 0.1521 1.0000
6.750 1.2198 0.02016 0.01140 -0.0901 0.0400 1.0000
7.000 1.2370 0.02169 0.01301 -0.0884 0.0323 1.0000
7.250 1.2563 0.02275 0.01422 -0.0871 0.0285 1.0000
7.500 1.2726 0.02412 0.01570 -0.0854 0.0263 1.0000
7.750 1.2837 0.02604 0.01771 -0.0831 0.0248 1.0000
8.000 1.2947 0.02809 0.01988 -0.0807 0.0240 1.0000
8.250 1.3101 0.02968 0.02159 -0.0789 0.0235 1.0000
8.500 1.3256 0.03150 0.02353 -0.0770 0.0230 1.0000
8.750 1.3417 0.03337 0.02553 -0.0754 0.0224 1.0000
9.000 1.3574 0.03511 0.02744 -0.0737 0.0214 1.0000
9.250 1.3720 0.03696 0.02944 -0.0721 0.0204 1.0000
9.500 1.3860 0.03938 0.03207 -0.0704 0.0201 1.0000
9.750 1.3980 0.04214 0.03513 -0.0684 0.0201 1.0000
10.000 1.4062 0.04527 0.03859 -0.0662 0.0203 1.0000
10.250 1.4086 0.04871 0.04240 -0.0634 0.0206 1.0000
10.500 1.4031 0.05215 0.04618 -0.0599 0.0210 1.0000
10.750 1.3931 0.05571 0.05007 -0.0565 0.0214 1.0000
11.000 1.3797 0.05953 0.05418 -0.0536 0.0218 1.0000
11.250 1.3641 0.06366 0.05858 -0.0514 0.0222 1.0000
11.500 1.3470 0.06819 0.06336 -0.0503 0.0225 1.0000
11.750 1.3283 0.07323 0.06864 -0.0501 0.0228 1.0000
12.000 1.3085 0.07884 0.07446 -0.0511 0.0231 1.0000
12.250 1.2879 0.08502 0.08083 -0.0530 0.0234 1.0000
12.500 1.2664 0.09192 0.08791 -0.0558 0.0236 1.0000
12.750 1.2706 0.09536 0.09151 -0.0564 0.0253 1.0000
13.000 1.2455 0.10336 0.09974 -0.0617 0.0256 1.0000
13.250 1.2207 0.11224 0.10880 -0.0679 0.0257 1.0000
13.500 1.1961 0.12219 0.11891 -0.0751 0.0258 1.0000
13.750 1.1700 0.13380 0.13067 -0.0836 0.0258 1.0000
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Polar data table (+)
Polar graphs
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