BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.49 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50sm-il-1000000.txt Download as CSV file: xf-be50sm-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2889 0.08906 0.08752 -0.0278 1.0000 0.0108
-8.750 -0.2872 0.08542 0.08390 -0.0285 1.0000 0.0109
-8.500 -0.2934 0.08029 0.07879 -0.0287 1.0000 0.0113
-8.250 -0.2909 0.07766 0.07618 -0.0283 1.0000 0.0115
-8.000 -0.2905 0.07524 0.07378 -0.0276 1.0000 0.0116
-7.750 -0.2945 0.07298 0.07155 -0.0261 1.0000 0.0118
-7.500 -0.2949 0.07028 0.06888 -0.0260 0.9994 0.0120
-7.250 -0.2847 0.06602 0.06462 -0.0294 0.9973 0.0123
-6.000 -0.2036 0.01893 0.01592 -0.1018 0.9857 0.0099
-5.750 -0.1672 0.01554 0.01199 -0.1051 0.9847 0.0104
-5.500 -0.1320 0.01422 0.01042 -0.1070 0.9837 0.0107
-5.250 -0.0996 0.01270 0.00861 -0.1083 0.9810 0.0110
-5.000 -0.0682 0.01058 0.00615 -0.1095 0.9774 0.0114
-4.750 -0.0363 0.00971 0.00514 -0.1105 0.9735 0.0120
-4.500 -0.0056 0.00933 0.00473 -0.1109 0.9678 0.0128
-4.250 0.0215 0.00898 0.00431 -0.1105 0.9581 0.0138
-4.000 0.0484 0.00861 0.00386 -0.1100 0.9479 0.0149
-3.750 0.0760 0.00799 0.00312 -0.1097 0.9388 0.0164
-3.500 0.1034 0.00768 0.00276 -0.1094 0.9293 0.0187
-3.250 0.1309 0.00750 0.00254 -0.1091 0.9190 0.0209
-3.000 0.1587 0.00720 0.00215 -0.1089 0.9084 0.0235
-2.750 0.1864 0.00702 0.00194 -0.1087 0.8970 0.0275
-2.500 0.2141 0.00695 0.00181 -0.1084 0.8843 0.0300
-2.250 0.2422 0.00671 0.00153 -0.1083 0.8705 0.0377
-2.000 0.2702 0.00657 0.00135 -0.1081 0.8556 0.0480
-1.750 0.2983 0.00646 0.00123 -0.1080 0.8396 0.0645
-1.500 0.3263 0.00635 0.00113 -0.1079 0.8219 0.0898
-1.250 0.3542 0.00628 0.00106 -0.1078 0.8029 0.1194
-1.000 0.3822 0.00621 0.00101 -0.1077 0.7833 0.1545
-0.750 0.4102 0.00611 0.00098 -0.1077 0.7621 0.2086
-0.500 0.4383 0.00594 0.00097 -0.1079 0.7407 0.3029
-0.250 0.4663 0.00584 0.00100 -0.1079 0.7178 0.3889
0.000 0.4941 0.00582 0.00104 -0.1079 0.6944 0.4536
0.250 0.5219 0.00583 0.00107 -0.1078 0.6702 0.5061
0.500 0.5496 0.00581 0.00112 -0.1078 0.6448 0.5739
0.750 0.5724 0.00513 0.00122 -0.1067 0.6205 0.8906
1.000 0.5978 0.00514 0.00120 -0.1059 0.5941 1.0000
1.250 0.6253 0.00533 0.00125 -0.1057 0.5653 1.0000
1.500 0.6528 0.00554 0.00131 -0.1056 0.5345 1.0000
1.750 0.6801 0.00578 0.00138 -0.1055 0.5012 1.0000
2.000 0.7073 0.00602 0.00147 -0.1053 0.4676 1.0000
2.250 0.7344 0.00628 0.00157 -0.1052 0.4349 1.0000
2.500 0.7616 0.00652 0.00168 -0.1051 0.4077 1.0000
2.750 0.7889 0.00675 0.00179 -0.1049 0.3855 1.0000
3.000 0.8162 0.00696 0.00192 -0.1048 0.3661 1.0000
3.250 0.8436 0.00715 0.00204 -0.1047 0.3500 1.0000
3.500 0.8709 0.00735 0.00217 -0.1046 0.3352 1.0000
3.750 0.8982 0.00753 0.00231 -0.1045 0.3219 1.0000
4.000 0.9255 0.00772 0.00246 -0.1044 0.3097 1.0000
4.250 0.9527 0.00791 0.00261 -0.1043 0.2979 1.0000
4.500 0.9798 0.00811 0.00277 -0.1041 0.2866 1.0000
4.750 1.0069 0.00831 0.00293 -0.1040 0.2753 1.0000
5.000 1.0339 0.00851 0.00311 -0.1038 0.2634 1.0000
5.250 1.0602 0.00879 0.00330 -0.1036 0.2424 1.0000
5.500 1.0865 0.00907 0.00350 -0.1034 0.2226 1.0000
5.750 1.1128 0.00934 0.00372 -0.1031 0.2079 1.0000
6.000 1.1388 0.00966 0.00397 -0.1029 0.1902 1.0000
6.250 1.1646 0.00998 0.00423 -0.1026 0.1723 1.0000
6.500 1.1897 0.01040 0.00455 -0.1022 0.1504 1.0000
6.750 1.2140 0.01091 0.00493 -0.1017 0.1236 1.0000
7.000 1.2368 0.01165 0.00545 -0.1010 0.0864 1.0000
7.250 1.2570 0.01276 0.00625 -0.1000 0.0393 1.0000
7.500 1.2793 0.01356 0.00695 -0.0992 0.0210 1.0000
7.750 1.3029 0.01413 0.00751 -0.0985 0.0166 1.0000
8.000 1.3265 0.01469 0.00812 -0.0978 0.0141 1.0000
8.250 1.3505 0.01515 0.00863 -0.0972 0.0128 1.0000
8.500 1.3735 0.01573 0.00925 -0.0965 0.0115 1.0000
8.750 1.3933 0.01676 0.01041 -0.0952 0.0100 1.0000
9.000 1.4167 0.01720 0.01090 -0.0945 0.0095 1.0000
9.250 1.4392 0.01774 0.01148 -0.0938 0.0088 1.0000
9.500 1.4611 0.01830 0.01208 -0.0930 0.0081 1.0000
9.750 1.4808 0.01911 0.01295 -0.0918 0.0073 1.0000
10.000 1.4944 0.02058 0.01459 -0.0897 0.0066 1.0000
10.250 1.5146 0.02121 0.01529 -0.0886 0.0063 1.0000
10.500 1.5329 0.02200 0.01616 -0.0873 0.0060 1.0000
10.750 1.5495 0.02289 0.01714 -0.0857 0.0057 1.0000
11.000 1.5651 0.02382 0.01816 -0.0840 0.0054 1.0000
11.250 1.5792 0.02480 0.01921 -0.0822 0.0051 1.0000
11.500 1.5916 0.02583 0.02034 -0.0801 0.0049 1.0000
11.750 1.5990 0.02700 0.02159 -0.0773 0.0047 1.0000
12.000 1.5994 0.02849 0.02319 -0.0736 0.0046 1.0000
12.250 1.5947 0.03048 0.02533 -0.0696 0.0044 1.0000
12.500 1.5831 0.03324 0.02829 -0.0656 0.0043 1.0000
13.000 1.5645 0.03933 0.03472 -0.0604 0.0042 1.0000
13.250 1.5658 0.04165 0.03717 -0.0592 0.0041 1.0000
13.500 1.5643 0.04444 0.04009 -0.0584 0.0041 1.0000
13.750 1.5610 0.04767 0.04346 -0.0580 0.0040 1.0000
14.000 1.5564 0.05127 0.04720 -0.0581 0.0040 1.0000
14.250 1.5485 0.05557 0.05165 -0.0587 0.0039 1.0000
14.500 1.5388 0.06034 0.05657 -0.0597 0.0039 1.0000
14.750 1.5295 0.06533 0.06171 -0.0612 0.0038 1.0000
15.000 1.5160 0.07117 0.06770 -0.0632 0.0038 1.0000
15.250 1.5022 0.07728 0.07395 -0.0656 0.0038 1.0000
15.500 1.4848 0.08421 0.08104 -0.0684 0.0038 1.0000
15.750 1.4695 0.09105 0.08802 -0.0714 0.0038 1.0000
16.000 1.4515 0.09844 0.09555 -0.0746 0.0038 1.0000
16.250 1.4346 0.10585 0.10309 -0.0780 0.0038 1.0000
16.500 1.4177 0.11342 0.11079 -0.0816 0.0038 1.0000
16.750 1.3994 0.12135 0.11885 -0.0854 0.0038 1.0000
17.000 1.3820 0.12936 0.12698 -0.0895 0.0038 1.0000
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Polar data table (+)
Polar graphs
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