BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.87 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50sm-il-1000000-n5.txt Download as CSV file: xf-be50sm-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4105 0.10635 0.10468 -0.0144 1.0000 0.0054
-9.250 -0.4049 0.10295 0.10129 -0.0159 1.0000 0.0054
-8.250 -0.4536 0.02013 0.01721 -0.0988 0.9888 0.0054
-8.000 -0.4223 0.01817 0.01499 -0.1010 0.9866 0.0056
-7.750 -0.3907 0.01665 0.01325 -0.1029 0.9846 0.0058
-7.500 -0.3592 0.01538 0.01177 -0.1044 0.9824 0.0060
-7.250 -0.3305 0.01433 0.01052 -0.1051 0.9781 0.0062
-7.000 -0.3006 0.01334 0.00934 -0.1060 0.9744 0.0065
-6.750 -0.2700 0.01249 0.00833 -0.1069 0.9711 0.0067
-6.500 -0.2409 0.01175 0.00744 -0.1073 0.9668 0.0069
-6.250 -0.2123 0.01112 0.00667 -0.1076 0.9614 0.0071
-6.000 -0.1833 0.01057 0.00600 -0.1079 0.9564 0.0072
-5.750 -0.1553 0.01009 0.00540 -0.1079 0.9501 0.0074
-5.500 -0.1272 0.00965 0.00487 -0.1079 0.9436 0.0075
-5.250 -0.0990 0.00905 0.00415 -0.1080 0.9367 0.0080
-5.000 -0.0712 0.00875 0.00379 -0.1079 0.9289 0.0087
-4.750 -0.0434 0.00851 0.00350 -0.1078 0.9194 0.0094
-4.500 -0.0161 0.00827 0.00318 -0.1075 0.9054 0.0101
-4.250 0.0108 0.00809 0.00287 -0.1070 0.8854 0.0107
-4.000 0.0381 0.00786 0.00252 -0.1067 0.8622 0.0120
-3.750 0.0657 0.00773 0.00230 -0.1065 0.8414 0.0133
-3.500 0.0936 0.00763 0.00210 -0.1064 0.8226 0.0147
-3.250 0.1215 0.00753 0.00190 -0.1062 0.8032 0.0160
-3.000 0.1496 0.00743 0.00172 -0.1062 0.7836 0.0186
-2.750 0.1777 0.00738 0.00159 -0.1061 0.7637 0.0210
-2.500 0.2058 0.00733 0.00144 -0.1060 0.7432 0.0242
-2.250 0.2339 0.00728 0.00133 -0.1060 0.7218 0.0288
-2.000 0.2620 0.00726 0.00123 -0.1059 0.7007 0.0344
-1.750 0.2902 0.00725 0.00115 -0.1059 0.6795 0.0410
-1.500 0.3183 0.00724 0.00108 -0.1059 0.6576 0.0529
-1.250 0.3464 0.00724 0.00103 -0.1059 0.6347 0.0670
-1.000 0.3745 0.00725 0.00100 -0.1059 0.6121 0.0837
-0.750 0.4026 0.00726 0.00097 -0.1059 0.5888 0.1067
-0.500 0.4307 0.00725 0.00097 -0.1060 0.5651 0.1390
-0.250 0.4586 0.00728 0.00098 -0.1060 0.5396 0.1716
0.000 0.4866 0.00729 0.00100 -0.1061 0.5114 0.2195
0.250 0.5144 0.00730 0.00104 -0.1062 0.4825 0.2804
0.500 0.5422 0.00731 0.00112 -0.1063 0.4528 0.3539
0.750 0.5700 0.00738 0.00120 -0.1063 0.4263 0.4082
1.000 0.5976 0.00748 0.00128 -0.1063 0.4020 0.4472
1.250 0.6254 0.00756 0.00136 -0.1063 0.3813 0.4857
1.500 0.6532 0.00761 0.00145 -0.1063 0.3640 0.5311
1.750 0.6810 0.00762 0.00155 -0.1063 0.3486 0.5961
2.000 0.7020 0.00688 0.00165 -0.1047 0.3365 1.0000
2.250 0.7297 0.00704 0.00173 -0.1047 0.3238 1.0000
2.500 0.7575 0.00719 0.00182 -0.1046 0.3122 1.0000
2.750 0.7851 0.00735 0.00192 -0.1045 0.3016 1.0000
3.000 0.8128 0.00750 0.00203 -0.1045 0.2907 1.0000
3.250 0.8404 0.00765 0.00214 -0.1044 0.2817 1.0000
3.500 0.8679 0.00781 0.00226 -0.1043 0.2720 1.0000
3.750 0.8953 0.00798 0.00238 -0.1042 0.2623 1.0000
4.000 0.9228 0.00813 0.00253 -0.1041 0.2538 1.0000
4.250 0.9500 0.00832 0.00267 -0.1040 0.2444 1.0000
4.500 0.9772 0.00850 0.00282 -0.1039 0.2350 1.0000
4.750 1.0043 0.00868 0.00298 -0.1037 0.2260 1.0000
5.000 1.0312 0.00890 0.00318 -0.1036 0.2145 1.0000
5.250 1.0568 0.00929 0.00341 -0.1033 0.1857 1.0000
5.500 1.0820 0.00973 0.00369 -0.1029 0.1557 1.0000
5.750 1.1077 0.01010 0.00397 -0.1026 0.1367 1.0000
6.000 1.1326 0.01057 0.00432 -0.1022 0.1118 1.0000
6.250 1.1570 0.01111 0.00472 -0.1017 0.0852 1.0000
6.500 1.1808 0.01172 0.00518 -0.1012 0.0584 1.0000
6.750 1.2046 0.01233 0.00567 -0.1006 0.0366 1.0000
7.000 1.2288 0.01285 0.00613 -0.1001 0.0246 1.0000
7.250 1.2533 0.01330 0.00657 -0.0996 0.0181 1.0000
7.500 1.2778 0.01374 0.00700 -0.0991 0.0141 1.0000
7.750 1.3023 0.01416 0.00743 -0.0986 0.0119 1.0000
8.000 1.3264 0.01463 0.00792 -0.0980 0.0099 1.0000
8.250 1.3507 0.01503 0.00835 -0.0975 0.0091 1.0000
8.500 1.3746 0.01547 0.00884 -0.0969 0.0083 1.0000
8.750 1.3978 0.01598 0.00937 -0.0963 0.0075 1.0000
9.000 1.4202 0.01658 0.01002 -0.0955 0.0067 1.0000
9.250 1.4434 0.01703 0.01052 -0.0948 0.0064 1.0000
9.500 1.4661 0.01752 0.01107 -0.0941 0.0059 1.0000
9.750 1.4884 0.01804 0.01163 -0.0934 0.0054 1.0000
10.000 1.5099 0.01861 0.01225 -0.0925 0.0049 1.0000
10.250 1.5301 0.01930 0.01300 -0.0915 0.0044 1.0000
10.500 1.5497 0.02003 0.01380 -0.0903 0.0041 1.0000
10.750 1.5697 0.02065 0.01450 -0.0892 0.0040 1.0000
11.000 1.5888 0.02134 0.01525 -0.0881 0.0038 1.0000
11.250 1.6070 0.02207 0.01606 -0.0867 0.0035 1.0000
11.500 1.6242 0.02283 0.01690 -0.0853 0.0033 1.0000
11.750 1.6403 0.02363 0.01780 -0.0838 0.0032 1.0000
12.000 1.6550 0.02449 0.01873 -0.0820 0.0030 1.0000
12.250 1.6678 0.02540 0.01972 -0.0800 0.0029 1.0000
12.500 1.6761 0.02639 0.02079 -0.0773 0.0027 1.0000
12.750 1.6812 0.02757 0.02207 -0.0742 0.0026 1.0000
13.000 1.6832 0.02903 0.02365 -0.0710 0.0025 1.0000
13.250 1.6818 0.03085 0.02561 -0.0679 0.0024 1.0000
13.500 1.6850 0.03243 0.02730 -0.0656 0.0024 1.0000
13.750 1.6869 0.03424 0.02924 -0.0635 0.0023 1.0000
14.000 1.6877 0.03629 0.03140 -0.0617 0.0023 1.0000
14.250 1.6867 0.03869 0.03393 -0.0603 0.0023 1.0000
14.500 1.6843 0.04142 0.03679 -0.0592 0.0023 1.0000
14.750 1.6811 0.04445 0.03996 -0.0586 0.0022 1.0000
15.000 1.6752 0.04808 0.04374 -0.0585 0.0022 1.0000
15.250 1.6675 0.05219 0.04799 -0.0589 0.0022 1.0000
15.500 1.6562 0.05713 0.05309 -0.0600 0.0022 1.0000
15.750 1.6444 0.06242 0.05852 -0.0616 0.0021 1.0000
16.000 1.6284 0.06864 0.06490 -0.0638 0.0021 1.0000
16.250 1.6112 0.07536 0.07176 -0.0664 0.0021 1.0000
16.500 1.5921 0.08257 0.07912 -0.0694 0.0021 1.0000
16.750 1.5697 0.09058 0.08729 -0.0728 0.0021 1.0000
17.000 1.5460 0.09890 0.09575 -0.0763 0.0021 1.0000
17.250 1.5218 0.10739 0.10438 -0.0800 0.0021 1.0000
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