BE50 (original) (be50-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 200,000 Max Cl/Cd: 73.94 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50-il-200000-n5.txt Download as CSV file: xf-be50-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3764 0.08599 0.08262 -0.0236 1.0000 0.0171
-8.000 -0.3788 0.08295 0.07964 -0.0241 1.0000 0.0171
-7.750 -0.3792 0.07933 0.07608 -0.0261 1.0000 0.0176
-7.500 -0.3771 0.07505 0.07184 -0.0295 1.0000 0.0182
-7.250 -0.3715 0.06997 0.06680 -0.0342 1.0000 0.0189
-7.000 -0.3655 0.06529 0.06213 -0.0376 1.0000 0.0192
-6.750 -0.3423 0.05918 0.05597 -0.0454 0.9980 0.0195
-6.500 -0.3057 0.05366 0.05034 -0.0546 0.9943 0.0202
-6.250 -0.2667 0.04797 0.04451 -0.0638 0.9902 0.0214
-6.000 -0.2207 0.04045 0.03667 -0.0749 0.9871 0.0239
-5.750 -0.1715 0.02984 0.02527 -0.0862 0.9844 0.0252
-5.500 -0.1324 0.02610 0.02086 -0.0903 0.9810 0.0274
-5.250 -0.0936 0.02189 0.01593 -0.0944 0.9785 0.0288
-5.000 -0.0560 0.01943 0.01304 -0.0973 0.9763 0.0300
-4.750 -0.0222 0.01831 0.01174 -0.0990 0.9716 0.0321
-4.500 0.0152 0.01696 0.01010 -0.1011 0.9676 0.0331
-4.250 0.0542 0.01573 0.00860 -0.1034 0.9643 0.0340
-4.000 0.0866 0.01482 0.00753 -0.1042 0.9567 0.0350
-3.750 0.1231 0.01399 0.00657 -0.1059 0.9515 0.0361
-3.500 0.1538 0.01336 0.00584 -0.1063 0.9424 0.0372
-3.250 0.1869 0.01287 0.00527 -0.1072 0.9343 0.0394
-3.000 0.2183 0.01243 0.00476 -0.1077 0.9241 0.0408
-2.750 0.2485 0.01195 0.00423 -0.1080 0.9118 0.0419
-2.500 0.2788 0.01152 0.00374 -0.1083 0.8983 0.0448
-2.250 0.3091 0.01120 0.00338 -0.1085 0.8833 0.0496
-2.000 0.3393 0.01087 0.00305 -0.1087 0.8671 0.0631
-1.750 0.3686 0.01049 0.00283 -0.1088 0.8477 0.1205
-1.500 0.3975 0.01020 0.00266 -0.1087 0.8256 0.1876
-1.250 0.4254 0.00975 0.00260 -0.1088 0.8016 0.3234
-1.000 0.4524 0.00954 0.00258 -0.1084 0.7775 0.4405
-0.750 0.4786 0.00933 0.00257 -0.1078 0.7548 0.5467
-0.500 0.5024 0.00893 0.00256 -0.1067 0.7345 0.6906
-0.250 0.5245 0.00851 0.00242 -0.1047 0.7145 1.0000
0.250 0.5791 0.00885 0.00241 -0.1041 0.6747 1.0000
0.500 0.6062 0.00903 0.00245 -0.1038 0.6542 1.0000
0.750 0.6332 0.00922 0.00249 -0.1035 0.6327 1.0000
1.000 0.6600 0.00942 0.00255 -0.1031 0.6095 1.0000
1.250 0.6867 0.00963 0.00264 -0.1028 0.5836 1.0000
1.500 0.7131 0.00987 0.00273 -0.1024 0.5552 1.0000
1.750 0.7392 0.01015 0.00284 -0.1020 0.5265 1.0000
2.000 0.7653 0.01043 0.00300 -0.1017 0.4983 1.0000
2.250 0.7914 0.01072 0.00316 -0.1013 0.4642 1.0000
2.500 0.8169 0.01108 0.00334 -0.1009 0.4256 1.0000
2.750 0.8423 0.01146 0.00355 -0.1005 0.3985 1.0000
3.000 0.8680 0.01183 0.00383 -0.1002 0.3793 1.0000
3.250 0.8938 0.01219 0.00412 -0.0999 0.3638 1.0000
3.500 0.9198 0.01252 0.00442 -0.0996 0.3507 1.0000
3.750 0.9459 0.01284 0.00475 -0.0993 0.3395 1.0000
4.000 0.9718 0.01318 0.00509 -0.0990 0.3286 1.0000
4.250 0.9975 0.01354 0.00544 -0.0987 0.3184 1.0000
4.500 1.0233 0.01387 0.00580 -0.0984 0.3057 1.0000
4.750 1.0487 0.01421 0.00617 -0.0981 0.2876 1.0000
5.000 1.0743 0.01453 0.00652 -0.0978 0.2711 1.0000
5.250 1.0991 0.01491 0.00685 -0.0974 0.2462 1.0000
5.500 1.1228 0.01542 0.00722 -0.0969 0.2098 1.0000
5.750 1.1455 0.01611 0.00772 -0.0964 0.1713 1.0000
6.000 1.1660 0.01711 0.00845 -0.0956 0.1175 1.0000
6.250 1.1804 0.01907 0.00979 -0.0941 0.0336 1.0000
6.500 1.2013 0.02006 0.01078 -0.0931 0.0195 1.0000
6.750 1.2224 0.02097 0.01176 -0.0921 0.0158 1.0000
7.000 1.2430 0.02190 0.01280 -0.0911 0.0137 1.0000
7.250 1.2619 0.02302 0.01406 -0.0898 0.0122 1.0000
7.500 1.2796 0.02421 0.01548 -0.0884 0.0116 1.0000
7.750 1.2968 0.02537 0.01682 -0.0869 0.0112 1.0000
8.000 1.3120 0.02666 0.01829 -0.0852 0.0108 1.0000
8.250 1.3252 0.02808 0.01987 -0.0833 0.0104 1.0000
8.500 1.3370 0.02957 0.02150 -0.0812 0.0100 1.0000
8.750 1.3479 0.03107 0.02313 -0.0791 0.0094 1.0000
9.000 1.3570 0.03263 0.02480 -0.0769 0.0089 1.0000
9.250 1.3620 0.03433 0.02660 -0.0742 0.0084 1.0000
9.500 1.3641 0.03631 0.02869 -0.0712 0.0082 1.0000
9.750 1.3657 0.03857 0.03111 -0.0684 0.0080 1.0000
10.000 1.3665 0.04125 0.03393 -0.0658 0.0078 1.0000
10.250 1.3689 0.04385 0.03668 -0.0635 0.0077 1.0000
10.500 1.3713 0.04617 0.03922 -0.0616 0.0076 1.0000
10.750 1.3720 0.04874 0.04201 -0.0598 0.0075 1.0000
11.000 1.3709 0.05160 0.04509 -0.0583 0.0074 1.0000
11.250 1.3677 0.05477 0.04850 -0.0571 0.0074 1.0000
11.500 1.3626 0.05831 0.05227 -0.0563 0.0073 1.0000
11.750 1.3555 0.06223 0.05644 -0.0561 0.0073 1.0000
12.000 1.3467 0.06659 0.06103 -0.0564 0.0072 1.0000
12.250 1.3361 0.07139 0.06607 -0.0573 0.0072 1.0000
12.500 1.3243 0.07664 0.07154 -0.0589 0.0072 1.0000
12.750 1.3111 0.08237 0.07749 -0.0610 0.0072 1.0000
13.000 1.2970 0.08850 0.08383 -0.0636 0.0072 1.0000
13.250 1.2822 0.09510 0.09063 -0.0668 0.0072 1.0000
13.500 1.2670 0.10213 0.09784 -0.0705 0.0073 1.0000
13.750 1.2515 0.10966 0.10556 -0.0748 0.0073 1.0000
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Polar data table (+)
Polar graphs
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