BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 50,000 Max Cl/Cd: 38.93 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50sm-il-50000.txt Download as CSV file: xf-be50sm-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3840 0.10714 0.10047 -0.0189 1.0000 0.1649
-7.500 -0.3649 0.10132 0.09464 -0.0173 1.0000 0.1707
-7.250 -0.3677 0.09962 0.09305 -0.0176 1.0000 0.1775
-7.000 -0.3703 0.09736 0.09092 -0.0190 1.0000 0.1814
-6.750 -0.3616 0.09405 0.08762 -0.0177 1.0000 0.1914
-6.500 -0.3587 0.09107 0.08474 -0.0178 1.0000 0.1982
-6.250 -0.3616 0.08999 0.08377 -0.0213 1.0000 0.2083
-6.000 -0.3515 0.08590 0.07973 -0.0176 1.0000 0.2195
-5.750 -0.3471 0.08297 0.07688 -0.0171 1.0000 0.2296
-5.250 -0.3396 0.07786 0.07193 -0.0185 1.0000 0.2547
-5.000 -0.3338 0.07514 0.06927 -0.0183 1.0000 0.2690
-4.750 -0.3272 0.07231 0.06650 -0.0171 1.0000 0.2845
-4.500 -0.3203 0.06955 0.06380 -0.0156 1.0000 0.3017
-4.250 -0.3125 0.06713 0.06144 -0.0166 1.0000 0.3261
-4.000 -0.3045 0.06472 0.05907 -0.0153 1.0000 0.3525
-3.750 -0.2992 0.06175 0.05616 -0.0111 1.0000 0.3749
-3.500 -0.2944 0.05942 0.05390 -0.0081 1.0000 0.4141
-3.250 -0.2921 0.05708 0.05165 -0.0032 1.0000 0.4569
-3.000 -0.1436 0.04445 0.03783 -0.0544 1.0000 0.2451
-2.750 -0.0467 0.03389 0.02540 -0.0738 1.0000 0.1482
-2.500 -0.0088 0.03096 0.02180 -0.0766 1.0000 0.1519
-2.250 0.0246 0.02855 0.01902 -0.0780 1.0000 0.1548
-2.000 0.0577 0.02680 0.01678 -0.0791 1.0000 0.1666
-1.750 0.0885 0.02532 0.01506 -0.0798 1.0000 0.1827
-1.500 0.1193 0.02415 0.01370 -0.0805 1.0000 0.2092
-1.250 0.1501 0.02302 0.01257 -0.0809 1.0000 0.2490
-1.000 0.1820 0.02195 0.01182 -0.0815 1.0000 0.3354
-0.750 0.2063 0.01888 0.01099 -0.0789 1.0000 0.7746
-0.500 0.2226 0.01914 0.01059 -0.0778 1.0000 1.0000
-0.250 0.2471 0.01965 0.01067 -0.0780 1.0000 1.0000
0.000 0.2705 0.02022 0.01094 -0.0783 1.0000 1.0000
0.250 0.2930 0.02086 0.01134 -0.0785 1.0000 1.0000
0.500 0.3148 0.02157 0.01185 -0.0788 1.0000 1.0000
0.750 0.3358 0.02238 0.01250 -0.0791 1.0000 1.0000
1.000 0.3559 0.02328 0.01329 -0.0795 1.0000 1.0000
1.250 0.3784 0.02431 0.01423 -0.0805 0.9981 1.0000
1.500 0.4448 0.02531 0.01510 -0.0891 0.9747 1.0000
1.750 0.5062 0.02604 0.01576 -0.0962 0.9501 1.0000
2.000 0.5656 0.02646 0.01618 -0.1023 0.9248 1.0000
2.250 0.6250 0.02651 0.01627 -0.1077 0.8996 1.0000
2.500 0.6768 0.02633 0.01619 -0.1111 0.8724 1.0000
2.750 0.7236 0.02594 0.01589 -0.1129 0.8450 1.0000
3.000 0.7663 0.02542 0.01545 -0.1136 0.8173 1.0000
3.250 0.8050 0.02487 0.01500 -0.1132 0.7889 1.0000
3.500 0.8401 0.02440 0.01457 -0.1121 0.7598 1.0000
3.750 0.8720 0.02410 0.01426 -0.1106 0.7302 1.0000
4.000 0.9000 0.02413 0.01427 -0.1088 0.6994 1.0000
4.250 0.9266 0.02437 0.01454 -0.1071 0.6695 1.0000
4.500 0.9529 0.02473 0.01487 -0.1055 0.6413 1.0000
4.750 0.9796 0.02516 0.01524 -0.1041 0.6156 1.0000
5.000 1.0038 0.02588 0.01599 -0.1028 0.5897 1.0000
5.250 1.0280 0.02669 0.01691 -0.1016 0.5658 1.0000
5.500 1.0543 0.02737 0.01755 -0.1005 0.5446 1.0000
5.750 1.0769 0.02844 0.01877 -0.0994 0.5225 1.0000
6.000 1.1023 0.02930 0.01966 -0.0983 0.5029 1.0000
6.250 1.1248 0.03047 0.02099 -0.0972 0.4830 1.0000
6.500 1.1480 0.03161 0.02232 -0.0961 0.4638 1.0000
6.750 1.1729 0.03262 0.02338 -0.0949 0.4453 1.0000
7.000 1.1930 0.03407 0.02509 -0.0937 0.4256 1.0000
7.250 1.2154 0.03523 0.02640 -0.0923 0.4054 1.0000
7.500 1.2359 0.03642 0.02775 -0.0906 0.3831 1.0000
7.750 1.2564 0.03698 0.02841 -0.0885 0.3551 1.0000
8.000 1.2750 0.03670 0.02802 -0.0858 0.3191 1.0000
8.250 1.2881 0.03660 0.02791 -0.0827 0.2791 1.0000
8.500 1.2954 0.03674 0.02784 -0.0788 0.2289 1.0000
8.750 1.2973 0.03806 0.02869 -0.0745 0.1765 1.0000
9.000 1.3039 0.04056 0.03113 -0.0713 0.1427 1.0000
9.250 1.3170 0.04320 0.03353 -0.0692 0.1224 1.0000
9.500 1.3310 0.04617 0.03667 -0.0673 0.1088 1.0000
9.750 1.3468 0.04968 0.04050 -0.0655 0.1008 1.0000
10.000 1.3584 0.05367 0.04481 -0.0636 0.0954 1.0000
10.250 1.3624 0.05735 0.04895 -0.0613 0.0907 1.0000
10.500 1.3768 0.06126 0.05276 -0.0603 0.0853 1.0000
10.750 1.3702 0.06570 0.05777 -0.0575 0.0846 1.0000
11.000 1.3590 0.07031 0.06285 -0.0548 0.0843 1.0000
11.250 1.3430 0.07486 0.06775 -0.0523 0.0843 1.0000
11.500 1.3231 0.07931 0.07249 -0.0500 0.0846 1.0000
11.750 1.3019 0.08421 0.07761 -0.0489 0.0849 1.0000
12.000 1.2805 0.08964 0.08323 -0.0489 0.0853 1.0000
12.250 1.1874 0.10433 0.09841 -0.0599 0.0952 1.0000
12.500 1.1656 0.11329 0.10739 -0.0645 0.0970 1.0000
12.750 1.1498 0.12188 0.11593 -0.0687 0.0979 1.0000
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Polar data table (+)
Polar graphs
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