Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 100,000 Max Cl/Cd: 67.6 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bw3-il-100000.txt Download as CSV file: xf-bw3-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Bergey BW-3 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3642 0.11541 0.11004 -0.0192 1.0000 0.0651
-8.000 -0.3711 0.11549 0.11021 -0.0199 1.0000 0.0654
-7.750 -0.3697 0.11538 0.11018 -0.0243 1.0000 0.0656
-7.500 -0.3597 0.10831 0.10314 -0.0207 1.0000 0.0661
-7.250 -0.3507 0.10359 0.09843 -0.0187 1.0000 0.0670
-7.000 -0.3439 0.10050 0.09538 -0.0183 1.0000 0.0680
-6.750 -0.3376 0.09773 0.09267 -0.0183 1.0000 0.0693
-6.500 -0.3313 0.09521 0.09018 -0.0189 1.0000 0.0707
-6.250 -0.3244 0.09279 0.08781 -0.0199 1.0000 0.0724
-6.000 -0.3152 0.09095 0.08603 -0.0226 1.0000 0.0745
-5.750 -0.2877 0.09280 0.08784 -0.0371 1.0000 0.0759
-5.500 -0.2900 0.08772 0.08288 -0.0324 1.0000 0.0764
-5.250 -0.2924 0.08382 0.07905 -0.0275 1.0000 0.0772
-5.000 -0.2909 0.08113 0.07642 -0.0252 1.0000 0.0781
-4.750 -0.2865 0.07888 0.07421 -0.0243 1.0000 0.0793
-4.500 -0.2792 0.07668 0.07203 -0.0244 1.0000 0.0809
-4.250 -0.2680 0.07448 0.06984 -0.0257 1.0000 0.0828
-4.000 -0.2475 0.07251 0.06782 -0.0298 1.0000 0.0859
-3.750 -0.1940 0.07181 0.06685 -0.0442 1.0000 0.0880
-3.500 -0.1933 0.06758 0.06273 -0.0409 1.0000 0.0887
-3.250 -0.1889 0.06441 0.05963 -0.0385 1.0000 0.0900
-3.000 -0.1762 0.06203 0.05726 -0.0383 1.0000 0.0923
-2.750 -0.1503 0.05970 0.05488 -0.0415 0.9994 0.0965
-2.500 -0.0743 0.05682 0.05162 -0.0566 0.9951 0.1018
-2.250 -0.0486 0.05291 0.04776 -0.0583 0.9908 0.1039
-2.000 -0.0090 0.05014 0.04491 -0.0630 0.9859 0.1091
-1.750 0.0451 0.04727 0.04179 -0.0711 0.9814 0.1171
-1.500 0.0813 0.04479 0.03924 -0.0745 0.9755 0.1234
-1.250 0.1275 0.04227 0.03650 -0.0801 0.9701 0.1316
-1.000 0.1711 0.04010 0.03416 -0.0846 0.9649 0.1453
-0.750 0.2105 0.03819 0.03207 -0.0880 0.9583 0.1593
-0.500 0.2506 0.03606 0.02987 -0.0915 0.9539 0.1778
-0.250 0.2856 0.03452 0.02821 -0.0938 0.9463 0.2056
0.000 0.3269 0.03280 0.02641 -0.0972 0.9417 0.2510
0.250 0.3530 0.03118 0.02488 -0.0975 0.9333 0.3047
0.500 0.3889 0.02913 0.02293 -0.0992 0.9284 0.3887
0.750 0.4178 0.02763 0.02145 -0.0992 0.9195 0.4589
1.000 0.4701 0.02605 0.01969 -0.1037 0.9138 0.4760
1.250 0.5463 0.02580 0.01812 -0.1112 0.9050 0.2277
1.500 0.5976 0.02452 0.01658 -0.1148 0.8990 0.2107
1.750 0.6553 0.02320 0.01511 -0.1199 0.8955 0.2110
2.000 0.6917 0.02269 0.01454 -0.1211 0.8843 0.2081
2.250 0.7537 0.02156 0.01338 -0.1273 0.8798 0.2085
2.500 0.7912 0.02124 0.01308 -0.1288 0.8677 0.2136
2.750 0.8383 0.02070 0.01257 -0.1320 0.8573 0.2161
3.000 0.8906 0.01979 0.01173 -0.1357 0.8391 0.2195
3.250 0.9430 0.01869 0.01067 -0.1386 0.8123 0.2279
3.500 0.9734 0.01831 0.01038 -0.1379 0.7851 0.2368
3.750 1.0050 0.01787 0.00998 -0.1372 0.7564 0.2459
4.000 1.0333 0.01750 0.00965 -0.1360 0.7226 0.2572
4.250 1.0599 0.01719 0.00936 -0.1343 0.6794 0.2753
4.500 1.1087 0.01640 0.00917 -0.1376 0.5498 1.0000
4.750 1.1081 0.01838 0.00954 -0.1309 0.3213 1.0000
5.000 1.1102 0.02124 0.01090 -0.1262 0.1345 1.0000
5.250 1.1258 0.02273 0.01209 -0.1236 0.1145 1.0000
5.500 1.1436 0.02390 0.01321 -0.1214 0.1038 1.0000
5.750 1.1596 0.02527 0.01455 -0.1190 0.0980 1.0000
6.000 1.1782 0.02653 0.01580 -0.1169 0.0932 1.0000
6.250 1.1975 0.02807 0.01719 -0.1152 0.0885 1.0000
6.500 1.2210 0.02990 0.01892 -0.1143 0.0845 1.0000
6.750 1.2475 0.03143 0.02053 -0.1136 0.0819 1.0000
7.000 1.2755 0.03320 0.02237 -0.1132 0.0801 1.0000
7.250 1.3032 0.03513 0.02437 -0.1128 0.0779 1.0000
7.500 1.3292 0.03728 0.02655 -0.1124 0.0749 1.0000
7.750 1.3558 0.04013 0.02953 -0.1121 0.0735 1.0000
8.000 1.3797 0.04287 0.03256 -0.1111 0.0734 1.0000
8.250 1.4008 0.04538 0.03545 -0.1093 0.0740 1.0000
8.500 1.4195 0.04855 0.03895 -0.1076 0.0738 1.0000
8.750 1.4353 0.05225 0.04298 -0.1057 0.0733 1.0000
9.000 1.4384 0.05517 0.04691 -0.1005 0.0775 1.0000
9.250 1.4449 0.06060 0.05288 -0.0973 0.0827 1.0000
9.500 1.3515 0.05542 0.04883 -0.0790 0.0906 1.0000
11.250 1.1200 0.14602 0.14135 -0.1108 0.1940 1.0000
11.500 0.8820 0.14195 0.13751 -0.0878 0.1965 1.0000
11.750 0.8866 0.14507 0.14064 -0.0872 0.1925 1.0000
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Polar data table (+)
Polar graphs
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