BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 100,000 Max Cl/Cd: 60.5 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50sm-il-100000.txt Download as CSV file: xf-be50sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3577 0.09540 0.09060 -0.0222 1.0000 0.0762
-7.250 -0.3637 0.09396 0.08928 -0.0243 1.0000 0.0786
-7.000 -0.3655 0.09266 0.08809 -0.0329 1.0000 0.0797
-6.750 -0.3615 0.08780 0.08329 -0.0296 1.0000 0.0812
-6.500 -0.3535 0.08453 0.08005 -0.0250 1.0000 0.0841
-6.250 -0.3489 0.08187 0.07744 -0.0251 1.0000 0.0871
-6.000 -0.3439 0.07919 0.07478 -0.0281 1.0000 0.0912
-5.750 -0.3299 0.07521 0.07081 -0.0406 1.0000 0.0946
-5.500 -0.3288 0.07223 0.06789 -0.0343 1.0000 0.0963
-5.250 -0.3221 0.06965 0.06534 -0.0325 1.0000 0.0995
-5.000 -0.2914 0.06482 0.06032 -0.0468 1.0000 0.1087
-4.750 -0.2893 0.06212 0.05775 -0.0416 1.0000 0.1106
-4.500 -0.2786 0.05962 0.05527 -0.0405 1.0000 0.1154
-4.250 -0.2515 0.05521 0.05073 -0.0474 1.0000 0.1249
-4.000 -0.2223 0.05149 0.04682 -0.0533 1.0000 0.1379
-3.750 -0.2124 0.04924 0.04467 -0.0506 1.0000 0.1425
-3.500 -0.1898 0.04649 0.04183 -0.0526 1.0000 0.1587
-3.250 -0.1610 0.04343 0.03861 -0.0566 1.0000 0.1824
-3.000 -0.0560 0.02883 0.02179 -0.0748 1.0000 0.0791
-2.750 -0.0198 0.02569 0.01816 -0.0770 1.0000 0.0781
-2.500 -0.0606 0.03376 0.02828 -0.0670 1.0000 0.2116
-2.250 -0.0464 0.03309 0.02781 -0.0649 1.0000 0.2568
-2.000 0.0787 0.02077 0.01215 -0.0805 1.0000 0.0958
-1.750 0.1082 0.01990 0.01115 -0.0810 1.0000 0.1058
-1.500 0.1372 0.01924 0.01040 -0.0816 1.0000 0.1220
-1.250 0.1671 0.01850 0.00985 -0.0825 1.0000 0.1470
-1.000 0.2006 0.01785 0.00946 -0.0842 0.9991 0.2015
-0.750 0.2538 0.01620 0.00924 -0.0894 0.9951 0.5441
-0.500 0.2932 0.01522 0.00895 -0.0909 0.9837 1.0000
-0.250 0.3424 0.01541 0.00882 -0.0954 0.9717 1.0000
0.000 0.3894 0.01552 0.00869 -0.0992 0.9590 1.0000
0.250 0.4349 0.01555 0.00856 -0.1026 0.9460 1.0000
0.500 0.4795 0.01549 0.00837 -0.1056 0.9328 1.0000
0.750 0.5240 0.01534 0.00813 -0.1084 0.9198 1.0000
1.000 0.5649 0.01512 0.00786 -0.1102 0.9059 1.0000
1.250 0.6028 0.01486 0.00756 -0.1113 0.8910 1.0000
1.500 0.6383 0.01457 0.00724 -0.1118 0.8749 1.0000
1.750 0.6720 0.01426 0.00690 -0.1117 0.8579 1.0000
2.000 0.7002 0.01408 0.00671 -0.1107 0.8359 1.0000
2.250 0.7299 0.01385 0.00642 -0.1098 0.8145 1.0000
2.500 0.7566 0.01374 0.00625 -0.1084 0.7878 1.0000
2.750 0.7829 0.01370 0.00613 -0.1070 0.7587 1.0000
3.000 0.8082 0.01378 0.00613 -0.1055 0.7250 1.0000
3.250 0.8334 0.01394 0.00614 -0.1041 0.6895 1.0000
3.500 0.8580 0.01421 0.00625 -0.1027 0.6514 1.0000
3.750 0.8827 0.01459 0.00641 -0.1015 0.6151 1.0000
4.000 0.9070 0.01504 0.00674 -0.1004 0.5788 1.0000
4.250 0.9316 0.01555 0.00708 -0.0994 0.5472 1.0000
4.500 0.9563 0.01609 0.00748 -0.0986 0.5188 1.0000
4.750 0.9811 0.01666 0.00795 -0.0979 0.4934 1.0000
5.000 1.0062 0.01726 0.00844 -0.0972 0.4713 1.0000
5.250 1.0311 0.01787 0.00907 -0.0965 0.4501 1.0000
5.500 1.0563 0.01853 0.00965 -0.0959 0.4316 1.0000
5.750 1.0813 0.01921 0.01034 -0.0954 0.4137 1.0000
6.000 1.1060 0.01989 0.01107 -0.0947 0.3962 1.0000
6.250 1.1308 0.02061 0.01186 -0.0941 0.3798 1.0000
6.500 1.1553 0.02133 0.01263 -0.0935 0.3636 1.0000
6.750 1.1795 0.02205 0.01339 -0.0928 0.3474 1.0000
7.000 1.2021 0.02264 0.01404 -0.0918 0.3285 1.0000
7.250 1.2221 0.02291 0.01438 -0.0905 0.3046 1.0000
7.500 1.2413 0.02317 0.01480 -0.0890 0.2803 1.0000
7.750 1.2604 0.02347 0.01522 -0.0876 0.2566 1.0000
8.000 1.2780 0.02371 0.01564 -0.0860 0.2258 1.0000
8.250 1.2910 0.02439 0.01622 -0.0839 0.1607 1.0000
8.500 1.2934 0.02748 0.01859 -0.0805 0.0898 1.0000
8.750 1.2998 0.02999 0.02092 -0.0775 0.0735 1.0000
9.000 1.3109 0.03195 0.02293 -0.0752 0.0633 1.0000
9.250 1.3227 0.03420 0.02530 -0.0728 0.0575 1.0000
9.500 1.3374 0.03641 0.02755 -0.0708 0.0532 1.0000
9.750 1.3567 0.03988 0.03094 -0.0697 0.0497 1.0000
10.000 1.3715 0.04198 0.03343 -0.0677 0.0467 1.0000
10.250 1.3858 0.04454 0.03624 -0.0660 0.0439 1.0000
10.500 1.3998 0.04770 0.03966 -0.0643 0.0425 1.0000
10.750 1.4103 0.05120 0.04345 -0.0625 0.0416 1.0000
11.000 1.4155 0.05497 0.04757 -0.0602 0.0412 1.0000
11.250 1.4154 0.05883 0.05176 -0.0577 0.0408 1.0000
11.500 1.4103 0.06285 0.05609 -0.0551 0.0403 1.0000
11.750 1.3980 0.06676 0.06027 -0.0520 0.0400 1.0000
12.000 1.3822 0.07069 0.06448 -0.0493 0.0399 1.0000
12.250 1.3641 0.07457 0.06864 -0.0473 0.0399 1.0000
12.500 1.3442 0.07882 0.07315 -0.0463 0.0399 1.0000
12.750 1.3224 0.08338 0.07800 -0.0465 0.0402 1.0000
13.000 1.1302 0.08605 0.08131 -0.0361 0.0446 1.0000
13.250 1.0951 0.09321 0.08867 -0.0390 0.0452 1.0000
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Polar data table (+)
Polar graphs
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