BE50 (original) (be50-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.18 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50-il-1000000.txt Download as CSV file: xf-be50-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4773 0.14907 0.14735 0.0044 1.0000 0.0086
-12.750 -0.4706 0.14550 0.14380 0.0029 1.0000 0.0091
-12.500 -0.4643 0.14146 0.13976 0.0008 1.0000 0.0097
-7.250 -0.2861 0.01926 0.01614 -0.0975 0.9893 0.0143
-7.000 -0.2523 0.01918 0.01607 -0.0990 0.9878 0.0148
-6.750 -0.2172 0.01922 0.01612 -0.1007 0.9864 0.0154
-6.500 -0.1814 0.01847 0.01526 -0.1029 0.9853 0.0164
-6.250 -0.1458 0.01675 0.01326 -0.1051 0.9841 0.0177
-6.000 -0.1131 0.01621 0.01256 -0.1062 0.9817 0.0184
-5.750 -0.0826 0.01301 0.00889 -0.1079 0.9779 0.0197
-5.500 -0.0521 0.01262 0.00847 -0.1086 0.9740 0.0208
-5.250 -0.0217 0.01205 0.00782 -0.1091 0.9702 0.0216
-5.000 0.0056 0.01124 0.00688 -0.1089 0.9642 0.0222
-4.750 0.0331 0.01051 0.00604 -0.1087 0.9585 0.0228
-4.500 0.0603 0.01003 0.00547 -0.1083 0.9522 0.0237
-4.250 0.0869 0.00963 0.00500 -0.1078 0.9440 0.0245
-4.000 0.1139 0.00922 0.00451 -0.1074 0.9355 0.0250
-3.750 0.1407 0.00888 0.00410 -0.1069 0.9260 0.0253
-3.500 0.1679 0.00859 0.00375 -0.1065 0.9138 0.0255
-3.250 0.1955 0.00780 0.00284 -0.1063 0.8988 0.0261
-3.000 0.2232 0.00728 0.00220 -0.1061 0.8780 0.0272
-2.750 0.2505 0.00705 0.00184 -0.1057 0.8525 0.0290
-2.500 0.2779 0.00694 0.00159 -0.1054 0.8233 0.0305
-2.250 0.3053 0.00692 0.00141 -0.1051 0.7922 0.0319
-2.000 0.3329 0.00692 0.00126 -0.1048 0.7625 0.0334
-1.750 0.3607 0.00695 0.00116 -0.1047 0.7363 0.0348
-1.500 0.3889 0.00690 0.00102 -0.1046 0.7140 0.0453
-1.250 0.4175 0.00662 0.00099 -0.1049 0.6939 0.1479
-1.000 0.4458 0.00655 0.00099 -0.1050 0.6743 0.2027
-0.750 0.4741 0.00640 0.00100 -0.1052 0.6547 0.2932
-0.500 0.5023 0.00628 0.00107 -0.1054 0.6332 0.4029
0.000 0.5583 0.00629 0.00116 -0.1054 0.5894 0.5023
0.250 0.5862 0.00620 0.00123 -0.1055 0.5660 0.5962
0.500 0.6071 0.00543 0.00128 -0.1038 0.5449 1.0000
0.750 0.6348 0.00561 0.00133 -0.1038 0.5220 1.0000
1.000 0.6625 0.00580 0.00139 -0.1037 0.4976 1.0000
1.250 0.6901 0.00601 0.00146 -0.1037 0.4634 1.0000
1.500 0.7166 0.00639 0.00157 -0.1035 0.4053 1.0000
1.750 0.7436 0.00669 0.00171 -0.1034 0.3747 1.0000
2.000 0.7710 0.00691 0.00183 -0.1034 0.3569 1.0000
2.250 0.7987 0.00708 0.00196 -0.1033 0.3449 1.0000
2.500 0.8262 0.00726 0.00208 -0.1033 0.3331 1.0000
2.750 0.8537 0.00745 0.00221 -0.1032 0.3210 1.0000
3.250 0.9085 0.00781 0.00248 -0.1032 0.2967 1.0000
3.500 0.9359 0.00798 0.00261 -0.1031 0.2839 1.0000
3.750 0.9632 0.00815 0.00275 -0.1031 0.2717 1.0000
4.000 0.9900 0.00840 0.00291 -0.1030 0.2511 1.0000
4.250 1.0166 0.00868 0.00309 -0.1028 0.2277 1.0000
4.500 1.0428 0.00901 0.00331 -0.1027 0.2032 1.0000
4.750 1.0685 0.00940 0.00357 -0.1024 0.1778 1.0000
5.000 1.0931 0.00997 0.00394 -0.1021 0.1404 1.0000
5.250 1.1144 0.01106 0.00459 -0.1013 0.0681 1.0000
5.500 1.1355 0.01220 0.00540 -0.1004 0.0159 1.0000
5.750 1.1608 0.01263 0.00584 -0.1000 0.0122 1.0000
6.000 1.1861 0.01304 0.00630 -0.0996 0.0113 1.0000
6.250 1.2110 0.01351 0.00683 -0.0991 0.0105 1.0000
6.500 1.2351 0.01408 0.00746 -0.0986 0.0096 1.0000
6.750 1.2571 0.01498 0.00849 -0.0976 0.0086 1.0000
7.000 1.2812 0.01546 0.00901 -0.0971 0.0083 1.0000
7.250 1.3044 0.01608 0.00970 -0.0964 0.0080 1.0000
7.500 1.3267 0.01678 0.01048 -0.0956 0.0076 1.0000
7.750 1.3483 0.01753 0.01131 -0.0947 0.0073 1.0000
8.000 1.3691 0.01833 0.01218 -0.0937 0.0070 1.0000
8.250 1.3890 0.01919 0.01311 -0.0927 0.0067 1.0000
8.500 1.4074 0.02019 0.01418 -0.0914 0.0064 1.0000
8.750 1.4220 0.02157 0.01564 -0.0895 0.0062 1.0000
9.000 1.4264 0.02412 0.01835 -0.0862 0.0059 1.0000
9.250 1.4396 0.02558 0.01993 -0.0842 0.0057 1.0000
9.500 1.4572 0.02637 0.02081 -0.0829 0.0056 1.0000
9.750 1.4726 0.02732 0.02187 -0.0813 0.0054 1.0000
10.000 1.4855 0.02849 0.02314 -0.0793 0.0052 1.0000
10.250 1.4946 0.02983 0.02460 -0.0769 0.0051 1.0000
10.500 1.4983 0.03137 0.02627 -0.0736 0.0050 1.0000
10.750 1.5004 0.03311 0.02814 -0.0704 0.0050 1.0000
11.000 1.5017 0.03499 0.03017 -0.0675 0.0049 1.0000
11.250 1.5015 0.03709 0.03242 -0.0648 0.0048 1.0000
11.500 1.4997 0.03946 0.03495 -0.0624 0.0048 1.0000
11.750 1.4963 0.04211 0.03776 -0.0603 0.0048 1.0000
12.000 1.4912 0.04511 0.04092 -0.0586 0.0047 1.0000
12.250 1.4848 0.04846 0.04444 -0.0575 0.0047 1.0000
12.500 1.4777 0.05207 0.04821 -0.0570 0.0047 1.0000
12.750 1.4665 0.05656 0.05290 -0.0570 0.0047 1.0000
13.000 1.4559 0.06117 0.05767 -0.0578 0.0047 1.0000
13.250 1.4429 0.06647 0.06314 -0.0592 0.0046 1.0000
13.500 1.4283 0.07226 0.06910 -0.0611 0.0046 1.0000
13.750 1.4119 0.07867 0.07568 -0.0637 0.0047 1.0000
14.000 1.3933 0.08584 0.08304 -0.0669 0.0047 1.0000
14.250 1.3741 0.09348 0.09084 -0.0706 0.0047 1.0000
14.500 1.3546 0.10168 0.09919 -0.0749 0.0047 1.0000
14.750 1.3353 0.11024 0.10790 -0.0795 0.0048 1.0000
15.000 1.3164 0.11899 0.11679 -0.0844 0.0048 1.0000
15.250 1.2954 0.12855 0.12649 -0.0898 0.0049 1.0000
15.500 1.2742 0.13854 0.13662 -0.0956 0.0049 1.0000
15.750 1.2549 0.14850 0.14671 -0.1015 0.0050 1.0000
16.000 1.2351 0.15928 0.15761 -0.1080 0.0051 1.0000
16.250 1.2145 0.17112 0.16955 -0.1151 0.0052 1.0000
16.500 1.1887 0.18578 0.18431 -0.1237 0.0054 1.0000
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Polar data table (+)
Polar graphs
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