BE50 (original) (be50-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 500,000 Max Cl/Cd: 95.39 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50-il-500000-n5.txt Download as CSV file: xf-be50-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3933 0.08561 0.08343 -0.0234 1.0000 0.0082
-8.500 -0.4019 0.08221 0.08009 -0.0232 1.0000 0.0085
-8.250 -0.4110 0.07833 0.07626 -0.0239 1.0000 0.0088
-8.000 -0.3932 0.06828 0.06621 -0.0378 0.9951 0.0092
-7.750 -0.3664 0.06356 0.06146 -0.0461 0.9913 0.0095
-7.500 -0.2998 0.01911 0.01509 -0.1007 0.9849 0.0133
-7.250 -0.2686 0.01934 0.01538 -0.1014 0.9820 0.0139
-7.000 -0.2367 0.01941 0.01544 -0.1024 0.9794 0.0146
-6.750 -0.2040 0.01847 0.01430 -0.1040 0.9772 0.0156
-6.500 -0.1723 0.01731 0.01290 -0.1053 0.9747 0.0170
-6.250 -0.1422 0.01662 0.01203 -0.1059 0.9701 0.0181
-6.000 -0.1102 0.01617 0.01142 -0.1068 0.9659 0.0187
-5.750 -0.0800 0.01395 0.00885 -0.1081 0.9609 0.0201
-5.500 -0.0509 0.01342 0.00824 -0.1085 0.9549 0.0211
-5.250 -0.0213 0.01279 0.00749 -0.1088 0.9491 0.0218
-5.000 0.0069 0.01213 0.00669 -0.1089 0.9414 0.0224
-4.750 0.0353 0.01159 0.00605 -0.1089 0.9338 0.0233
-4.500 0.0633 0.01106 0.00540 -0.1088 0.9246 0.0241
-4.250 0.0911 0.01050 0.00474 -0.1086 0.9133 0.0247
-4.000 0.1187 0.01004 0.00418 -0.1083 0.8985 0.0253
-3.750 0.1461 0.00966 0.00368 -0.1080 0.8808 0.0259
-3.500 0.1736 0.00936 0.00326 -0.1076 0.8603 0.0265
-3.250 0.2007 0.00913 0.00289 -0.1072 0.8357 0.0270
-3.000 0.2279 0.00897 0.00258 -0.1069 0.8092 0.0273
-2.750 0.2551 0.00887 0.00230 -0.1065 0.7814 0.0277
-2.500 0.2827 0.00876 0.00204 -0.1063 0.7554 0.0285
-2.250 0.3106 0.00864 0.00176 -0.1062 0.7332 0.0304
-2.000 0.3384 0.00860 0.00157 -0.1060 0.7114 0.0323
-1.750 0.3663 0.00857 0.00145 -0.1059 0.6911 0.0357
-1.500 0.3942 0.00857 0.00137 -0.1058 0.6716 0.0412
-1.250 0.4222 0.00845 0.00131 -0.1059 0.6525 0.0865
-1.000 0.4503 0.00834 0.00131 -0.1060 0.6337 0.1469
-0.750 0.4782 0.00832 0.00131 -0.1060 0.6154 0.1816
-0.500 0.5061 0.00828 0.00132 -0.1060 0.5959 0.2289
-0.250 0.5341 0.00803 0.00143 -0.1063 0.5746 0.3949
0.250 0.5890 0.00803 0.00159 -0.1063 0.5259 0.5352
0.500 0.6162 0.00803 0.00167 -0.1062 0.5016 0.5984
0.750 0.6358 0.00733 0.00171 -0.1042 0.4758 1.0000
1.000 0.6625 0.00763 0.00178 -0.1040 0.4268 1.0000
1.250 0.6891 0.00797 0.00190 -0.1038 0.3895 1.0000
1.500 0.7162 0.00823 0.00203 -0.1037 0.3678 1.0000
1.750 0.7435 0.00845 0.00216 -0.1037 0.3538 1.0000
2.000 0.7708 0.00865 0.00230 -0.1036 0.3420 1.0000
2.250 0.7981 0.00885 0.00244 -0.1035 0.3315 1.0000
2.500 0.8256 0.00903 0.00259 -0.1034 0.3229 1.0000
2.750 0.8529 0.00921 0.00276 -0.1034 0.3153 1.0000
3.000 0.8800 0.00941 0.00292 -0.1033 0.3057 1.0000
3.250 0.9073 0.00960 0.00309 -0.1032 0.2955 1.0000
3.500 0.9342 0.00982 0.00327 -0.1031 0.2810 1.0000
3.750 0.9606 0.01010 0.00347 -0.1029 0.2605 1.0000
4.000 0.9873 0.01035 0.00367 -0.1028 0.2419 1.0000
4.250 1.0132 0.01069 0.00390 -0.1026 0.2176 1.0000
4.500 1.0388 0.01108 0.00417 -0.1024 0.1930 1.0000
4.750 1.0630 0.01167 0.00457 -0.1020 0.1543 1.0000
5.000 1.0859 0.01244 0.00506 -0.1014 0.1060 1.0000
5.250 1.1056 0.01377 0.00593 -0.1005 0.0326 1.0000
5.500 1.1291 0.01446 0.00652 -0.0999 0.0140 1.0000
5.750 1.1538 0.01492 0.00702 -0.0994 0.0109 1.0000
6.000 1.1783 0.01541 0.00761 -0.0989 0.0095 1.0000
6.250 1.2021 0.01600 0.00828 -0.0983 0.0085 1.0000
6.500 1.2248 0.01674 0.00913 -0.0976 0.0076 1.0000
6.750 1.2482 0.01732 0.00979 -0.0969 0.0073 1.0000
7.000 1.2709 0.01797 0.01053 -0.0962 0.0069 1.0000
7.250 1.2931 0.01864 0.01130 -0.0954 0.0063 1.0000
7.500 1.3147 0.01935 0.01208 -0.0946 0.0057 1.0000
7.750 1.3348 0.02022 0.01303 -0.0936 0.0054 1.0000
8.000 1.3523 0.02137 0.01428 -0.0922 0.0051 1.0000
8.250 1.3675 0.02270 0.01572 -0.0905 0.0049 1.0000
8.500 1.3851 0.02366 0.01679 -0.0891 0.0048 1.0000
8.750 1.4011 0.02475 0.01798 -0.0875 0.0046 1.0000
9.000 1.4153 0.02595 0.01933 -0.0857 0.0044 1.0000
9.250 1.4277 0.02724 0.02075 -0.0837 0.0043 1.0000
9.500 1.4383 0.02862 0.02226 -0.0815 0.0041 1.0000
9.750 1.4459 0.03006 0.02382 -0.0788 0.0040 1.0000
10.000 1.4502 0.03154 0.02543 -0.0757 0.0039 1.0000
10.250 1.4541 0.03311 0.02713 -0.0729 0.0038 1.0000
10.500 1.4578 0.03473 0.02889 -0.0704 0.0037 1.0000
10.750 1.4611 0.03646 0.03074 -0.0681 0.0036 1.0000
11.000 1.4637 0.03833 0.03273 -0.0662 0.0035 1.0000
11.250 1.4656 0.04036 0.03487 -0.0646 0.0034 1.0000
11.500 1.4651 0.04280 0.03744 -0.0632 0.0033 1.0000
11.750 1.4629 0.04560 0.04036 -0.0622 0.0032 1.0000
12.000 1.4577 0.04900 0.04391 -0.0615 0.0032 1.0000
12.250 1.4483 0.05317 0.04825 -0.0613 0.0031 1.0000
12.500 1.4381 0.05770 0.05296 -0.0615 0.0031 1.0000
12.750 1.4309 0.06207 0.05751 -0.0623 0.0030 1.0000
13.000 1.4222 0.06688 0.06253 -0.0636 0.0030 1.0000
13.250 1.4114 0.07216 0.06798 -0.0652 0.0030 1.0000
13.500 1.3998 0.07782 0.07382 -0.0673 0.0030 1.0000
13.750 1.3871 0.08391 0.08009 -0.0698 0.0030 1.0000
14.000 1.3732 0.09041 0.08675 -0.0726 0.0030 1.0000
14.250 1.3589 0.09733 0.09383 -0.0758 0.0030 1.0000
14.500 1.3446 0.10452 0.10118 -0.0794 0.0030 1.0000
14.750 1.3297 0.11199 0.10880 -0.0831 0.0030 1.0000
15.000 1.3151 0.11961 0.11656 -0.0870 0.0030 1.0000
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Polar data table (+)
Polar graphs
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