BE50 (original) (be50-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 50,000 Max Cl/Cd: 38.34 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50-il-50000.txt Download as CSV file: xf-be50-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3844 0.10048 0.09392 -0.0167 1.0000 0.1883
-7.750 -0.3710 0.09627 0.08972 -0.0149 1.0000 0.1976
-7.500 -0.3755 0.09447 0.08805 -0.0173 1.0000 0.2031
-7.250 -0.3663 0.09105 0.08467 -0.0159 1.0000 0.2133
-6.750 -0.3619 0.08586 0.07966 -0.0178 1.0000 0.2324
-6.500 -0.3581 0.08351 0.07738 -0.0189 1.0000 0.2462
-6.250 -0.3520 0.08061 0.07455 -0.0183 1.0000 0.2609
-6.000 -0.3454 0.07765 0.07162 -0.0174 1.0000 0.2759
-5.750 -0.3385 0.07467 0.06870 -0.0162 1.0000 0.2911
-5.500 -0.3312 0.07170 0.06579 -0.0143 1.0000 0.3073
-5.250 -0.3238 0.06897 0.06312 -0.0125 1.0000 0.3259
-5.000 -0.3169 0.06650 0.06070 -0.0125 1.0000 0.3499
-4.750 -0.3094 0.06416 0.05841 -0.0115 1.0000 0.3775
-4.500 -0.3041 0.06155 0.05588 -0.0078 1.0000 0.4073
-4.250 -0.3002 0.05898 0.05339 -0.0029 1.0000 0.4399
-3.750 -0.0958 0.03848 0.03068 -0.0682 1.0000 0.1746
-3.500 -0.0530 0.03427 0.02574 -0.0729 1.0000 0.1554
-3.250 -0.0194 0.03160 0.02263 -0.0751 1.0000 0.1538
-3.000 0.0146 0.02945 0.01993 -0.0769 1.0000 0.1559
-2.750 0.0473 0.02758 0.01758 -0.0781 1.0000 0.1565
-2.500 0.0776 0.02604 0.01568 -0.0788 1.0000 0.1598
-2.250 0.1068 0.02488 0.01435 -0.0793 1.0000 0.1679
-2.000 0.1358 0.02402 0.01328 -0.0797 1.0000 0.1871
-1.750 0.1660 0.02300 0.01224 -0.0801 1.0000 0.2172
-1.500 0.2040 0.02103 0.01129 -0.0817 1.0000 0.3960
-1.250 0.2129 0.01883 0.01065 -0.0772 1.0000 1.0000
-1.000 0.2378 0.01936 0.01062 -0.0776 1.0000 1.0000
-0.750 0.2611 0.01995 0.01087 -0.0779 1.0000 1.0000
-0.500 0.2834 0.02061 0.01127 -0.0782 1.0000 1.0000
-0.250 0.3051 0.02135 0.01177 -0.0785 1.0000 1.0000
0.000 0.3261 0.02215 0.01241 -0.0789 1.0000 1.0000
0.250 0.3464 0.02304 0.01316 -0.0793 1.0000 1.0000
0.500 0.3795 0.02403 0.01403 -0.0821 0.9945 1.0000
0.750 0.4391 0.02495 0.01481 -0.0894 0.9737 1.0000
1.000 0.4971 0.02567 0.01546 -0.0959 0.9522 1.0000
1.250 0.5527 0.02614 0.01592 -0.1014 0.9290 1.0000
1.500 0.6023 0.02639 0.01620 -0.1054 0.9037 1.0000
1.750 0.6533 0.02633 0.01621 -0.1090 0.8779 1.0000
2.000 0.7053 0.02591 0.01591 -0.1119 0.8522 1.0000
2.250 0.7527 0.02525 0.01534 -0.1132 0.8257 1.0000
2.500 0.7929 0.02464 0.01484 -0.1131 0.7968 1.0000
2.750 0.8275 0.02422 0.01446 -0.1119 0.7657 1.0000
3.000 0.8590 0.02399 0.01424 -0.1103 0.7338 1.0000
3.250 0.8880 0.02399 0.01421 -0.1086 0.7025 1.0000
3.500 0.9151 0.02424 0.01447 -0.1069 0.6724 1.0000
3.750 0.9406 0.02469 0.01490 -0.1053 0.6437 1.0000
4.000 0.9654 0.02527 0.01549 -0.1039 0.6168 1.0000
4.250 0.9904 0.02591 0.01613 -0.1026 0.5920 1.0000
4.500 1.0161 0.02650 0.01677 -0.1014 0.5691 1.0000
4.750 1.0395 0.02739 0.01777 -0.1003 0.5459 1.0000
5.000 1.0655 0.02809 0.01846 -0.0991 0.5255 1.0000
5.250 1.0879 0.02922 0.01976 -0.0981 0.5040 1.0000
5.500 1.1122 0.03018 0.02086 -0.0970 0.4842 1.0000
5.750 1.1363 0.03122 0.02202 -0.0960 0.4655 1.0000
6.000 1.1579 0.03250 0.02354 -0.0949 0.4462 1.0000
6.250 1.1816 0.03357 0.02476 -0.0937 0.4278 1.0000
6.500 1.2058 0.03465 0.02595 -0.0925 0.4095 1.0000
6.750 1.2253 0.03598 0.02761 -0.0910 0.3875 1.0000
7.000 1.2458 0.03539 0.02680 -0.0882 0.3497 1.0000
7.250 1.2572 0.03440 0.02566 -0.0847 0.3028 1.0000
7.500 1.2627 0.03372 0.02495 -0.0807 0.2531 1.0000
7.750 1.2539 0.03481 0.02568 -0.0753 0.1753 1.0000
8.000 1.2541 0.03792 0.02814 -0.0716 0.1269 1.0000
8.250 1.2676 0.04087 0.03104 -0.0693 0.1065 1.0000
8.500 1.2851 0.04381 0.03407 -0.0675 0.0950 1.0000
8.750 1.3027 0.04685 0.03715 -0.0661 0.0867 1.0000
9.000 1.3189 0.04997 0.04054 -0.0646 0.0810 1.0000
9.250 1.3410 0.05423 0.04481 -0.0640 0.0776 1.0000
9.500 1.3478 0.05834 0.04947 -0.0618 0.0767 1.0000
9.750 1.3492 0.06273 0.05439 -0.0595 0.0762 1.0000
10.000 1.3448 0.06728 0.05940 -0.0572 0.0761 1.0000
10.250 1.3349 0.07186 0.06438 -0.0549 0.0762 1.0000
10.500 1.3194 0.07627 0.06910 -0.0525 0.0764 1.0000
10.750 1.3011 0.08079 0.07387 -0.0507 0.0767 1.0000
11.000 1.2816 0.08575 0.07905 -0.0499 0.0771 1.0000
11.250 1.2626 0.09124 0.08471 -0.0501 0.0775 1.0000
11.500 1.1689 0.10536 0.09936 -0.0622 0.0823 1.0000
11.750 1.1253 0.11956 0.11360 -0.0723 0.0861 1.0000
12.000 1.1060 0.12994 0.12394 -0.0780 0.0882 1.0000
12.250 1.0969 0.13808 0.13200 -0.0815 0.0893 1.0000
12.500 0.8347 0.14695 0.14089 -0.0722 0.1245 1.0000
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Polar data table (+)
Polar graphs
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