BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 500,000 Max Cl/Cd: 97.79 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50sm-il-500000-n5.txt Download as CSV file: xf-be50sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3756 0.09257 0.09029 -0.0218 1.0000 0.0102
-8.000 -0.3716 0.08958 0.08732 -0.0228 1.0000 0.0099
-7.750 -0.3702 0.08655 0.08433 -0.0235 1.0000 0.0095
-7.500 -0.3744 0.08393 0.08175 -0.0229 1.0000 0.0093
-7.250 -0.3800 0.08129 0.07916 -0.0224 1.0000 0.0090
-6.250 -0.2374 0.01937 0.01541 -0.1004 0.9800 0.0087
-6.000 -0.2052 0.01690 0.01248 -0.1025 0.9766 0.0091
-5.750 -0.1724 0.01515 0.01036 -0.1042 0.9737 0.0095
-5.500 -0.1394 0.01408 0.00905 -0.1055 0.9711 0.0102
-5.250 -0.1081 0.01327 0.00803 -0.1064 0.9671 0.0107
-5.000 -0.0778 0.01211 0.00667 -0.1071 0.9620 0.0112
-4.750 -0.0462 0.01139 0.00584 -0.1080 0.9578 0.0120
-4.500 -0.0161 0.01091 0.00527 -0.1084 0.9523 0.0128
-4.250 0.0135 0.01044 0.00471 -0.1087 0.9458 0.0139
-4.000 0.0432 0.01003 0.00421 -0.1090 0.9391 0.0151
-3.750 0.0720 0.00954 0.00364 -0.1090 0.9286 0.0167
-3.500 0.0996 0.00929 0.00333 -0.1087 0.9134 0.0190
-3.250 0.1267 0.00911 0.00305 -0.1082 0.8951 0.0213
-3.000 0.1544 0.00879 0.00265 -0.1080 0.8790 0.0242
-2.750 0.1821 0.00862 0.00243 -0.1078 0.8637 0.0280
-2.500 0.2098 0.00846 0.00216 -0.1075 0.8474 0.0318
-2.250 0.2376 0.00830 0.00195 -0.1073 0.8303 0.0380
-2.000 0.2653 0.00819 0.00178 -0.1071 0.8121 0.0474
-1.750 0.2931 0.00810 0.00164 -0.1069 0.7929 0.0598
-1.500 0.3207 0.00804 0.00152 -0.1067 0.7726 0.0761
-1.250 0.3484 0.00797 0.00144 -0.1066 0.7516 0.1007
-0.750 0.4038 0.00787 0.00133 -0.1064 0.7075 0.1698
-0.500 0.4314 0.00780 0.00130 -0.1063 0.6848 0.2227
-0.250 0.4591 0.00770 0.00131 -0.1063 0.6609 0.3002
0.000 0.4867 0.00764 0.00136 -0.1063 0.6362 0.3830
0.250 0.5141 0.00766 0.00141 -0.1062 0.6114 0.4432
0.500 0.5414 0.00771 0.00146 -0.1061 0.5854 0.4916
0.750 0.5686 0.00774 0.00152 -0.1059 0.5579 0.5473
1.000 0.5956 0.00766 0.00161 -0.1058 0.5292 0.6472
1.250 0.6148 0.00711 0.00162 -0.1036 0.5012 1.0000
1.500 0.6419 0.00735 0.00169 -0.1034 0.4708 1.0000
1.750 0.6689 0.00760 0.00178 -0.1032 0.4415 1.0000
2.000 0.6959 0.00785 0.00189 -0.1030 0.4154 1.0000
2.250 0.7231 0.00808 0.00200 -0.1029 0.3934 1.0000
2.750 0.7773 0.00853 0.00226 -0.1026 0.3582 1.0000
3.000 0.8045 0.00874 0.00241 -0.1024 0.3434 1.0000
3.250 0.8316 0.00895 0.00255 -0.1023 0.3302 1.0000
3.500 0.8588 0.00915 0.00271 -0.1022 0.3179 1.0000
3.750 0.8859 0.00935 0.00287 -0.1020 0.3061 1.0000
4.000 0.9129 0.00956 0.00306 -0.1018 0.2956 1.0000
4.250 0.9398 0.00978 0.00324 -0.1017 0.2850 1.0000
4.750 0.9934 0.01021 0.00365 -0.1013 0.2643 1.0000
5.000 1.0200 0.01044 0.00388 -0.1010 0.2545 1.0000
5.250 1.0464 0.01070 0.00412 -0.1008 0.2442 1.0000
5.750 1.0979 0.01135 0.00464 -0.1002 0.2061 1.0000
6.000 1.1226 0.01183 0.00498 -0.0998 0.1762 1.0000
6.250 1.1475 0.01225 0.00532 -0.0994 0.1544 1.0000
6.500 1.1720 0.01273 0.00571 -0.0989 0.1325 1.0000
6.750 1.1953 0.01338 0.00620 -0.0983 0.1018 1.0000
7.000 1.2170 0.01424 0.00685 -0.0976 0.0654 1.0000
7.250 1.2386 0.01511 0.00757 -0.0967 0.0385 1.0000
7.500 1.2613 0.01578 0.00820 -0.0960 0.0261 1.0000
7.750 1.2843 0.01640 0.00882 -0.0953 0.0199 1.0000
8.000 1.3070 0.01703 0.00947 -0.0945 0.0162 1.0000
8.250 1.3296 0.01764 0.01015 -0.0937 0.0139 1.0000
8.500 1.3522 0.01822 0.01083 -0.0930 0.0125 1.0000
8.750 1.3737 0.01891 0.01156 -0.0921 0.0111 1.0000
9.000 1.3939 0.01974 0.01247 -0.0910 0.0098 1.0000
9.250 1.4152 0.02037 0.01319 -0.0901 0.0091 1.0000
9.500 1.4353 0.02110 0.01401 -0.0890 0.0084 1.0000
9.750 1.4546 0.02188 0.01488 -0.0878 0.0078 1.0000
10.000 1.4723 0.02279 0.01586 -0.0864 0.0073 1.0000
10.250 1.4856 0.02410 0.01731 -0.0845 0.0067 1.0000
10.500 1.5012 0.02506 0.01839 -0.0828 0.0065 1.0000
10.750 1.5156 0.02606 0.01951 -0.0810 0.0062 1.0000
11.000 1.5285 0.02711 0.02068 -0.0791 0.0058 1.0000
11.250 1.5390 0.02818 0.02185 -0.0768 0.0055 1.0000
11.500 1.5468 0.02925 0.02303 -0.0741 0.0052 1.0000
11.750 1.5540 0.03041 0.02429 -0.0716 0.0049 1.0000
12.000 1.5593 0.03177 0.02575 -0.0691 0.0047 1.0000
12.250 1.5618 0.03343 0.02753 -0.0666 0.0045 1.0000
12.500 1.5596 0.03561 0.02984 -0.0640 0.0044 1.0000
12.750 1.5528 0.03840 0.03281 -0.0617 0.0042 1.0000
13.000 1.5497 0.04111 0.03567 -0.0602 0.0042 1.0000
13.250 1.5474 0.04392 0.03864 -0.0592 0.0041 1.0000
13.500 1.5436 0.04716 0.04204 -0.0587 0.0041 1.0000
13.750 1.5381 0.05084 0.04589 -0.0587 0.0040 1.0000
14.000 1.5312 0.05497 0.05019 -0.0592 0.0039 1.0000
14.250 1.5224 0.05964 0.05503 -0.0603 0.0039 1.0000
14.500 1.5118 0.06479 0.06034 -0.0618 0.0039 1.0000
14.750 1.5004 0.07033 0.06604 -0.0637 0.0038 1.0000
15.000 1.4869 0.07639 0.07227 -0.0660 0.0038 1.0000
15.250 1.4726 0.08277 0.07881 -0.0685 0.0038 1.0000
15.500 1.4568 0.08960 0.08579 -0.0714 0.0037 1.0000
15.750 1.4415 0.09647 0.09280 -0.0743 0.0037 1.0000
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Polar data table (+)
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