Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 100,000 Max Cl/Cd: 58.41 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bw3-il-100000-n5.txt Download as CSV file: xf-bw3-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3532 0.10628 0.10094 -0.0185 1.0000 0.0502
-7.500 -0.3509 0.10392 0.09863 -0.0181 1.0000 0.0509
-7.250 -0.3489 0.10161 0.09638 -0.0177 1.0000 0.0516
-7.000 -0.3441 0.09909 0.09392 -0.0181 1.0000 0.0524
-6.750 -0.3384 0.09652 0.09140 -0.0189 1.0000 0.0536
-6.500 -0.3319 0.09406 0.08900 -0.0203 1.0000 0.0547
-6.250 -0.3235 0.09179 0.08678 -0.0231 1.0000 0.0558
-6.000 -0.3118 0.08972 0.08473 -0.0277 1.0000 0.0562
-5.500 -0.2998 0.08372 0.07886 -0.0273 1.0000 0.0572
-5.250 -0.2970 0.08137 0.07657 -0.0253 1.0000 0.0581
-5.000 -0.2740 0.07802 0.07320 -0.0292 0.9973 0.0592
-4.750 -0.2402 0.07414 0.06927 -0.0358 0.9927 0.0603
-4.500 -0.2050 0.07017 0.06522 -0.0428 0.9869 0.0610
-4.250 -0.1592 0.06503 0.05992 -0.0536 0.9794 0.0556
-4.000 -0.1311 0.06109 0.05594 -0.0573 0.9720 0.0523
-3.500 -0.0406 0.05101 0.04547 -0.0750 0.9568 0.0480
-3.250 -0.0008 0.04708 0.04136 -0.0807 0.9508 0.0479
-3.000 0.0355 0.04412 0.03830 -0.0849 0.9446 0.0493
-2.750 0.0711 0.04208 0.03619 -0.0881 0.9396 0.0524
-2.500 0.1122 0.03860 0.03247 -0.0930 0.9335 0.0536
-2.250 0.1624 0.03333 0.02668 -0.0995 0.9297 0.0565
-2.000 0.1930 0.03302 0.02643 -0.1008 0.9245 0.0598
-1.750 0.2317 0.03020 0.02329 -0.1037 0.9189 0.0628
-1.500 0.2712 0.02804 0.02086 -0.1066 0.9147 0.0680
-1.250 0.3114 0.02598 0.01845 -0.1093 0.9111 0.0735
-1.000 0.3451 0.02479 0.01707 -0.1106 0.9040 0.0793
-0.750 0.3860 0.02304 0.01481 -0.1131 0.8993 0.0884
-0.500 0.4265 0.02246 0.01427 -0.1160 0.8954 0.0941
-0.250 0.4614 0.02143 0.01282 -0.1171 0.8871 0.1019
0.000 0.5005 0.02071 0.01209 -0.1196 0.8813 0.1061
0.250 0.5366 0.02012 0.01126 -0.1211 0.8730 0.1129
0.500 0.5757 0.01938 0.01035 -0.1233 0.8649 0.1163
0.750 0.6095 0.01898 0.00994 -0.1245 0.8536 0.1203
1.000 0.6466 0.01856 0.00940 -0.1261 0.8424 0.1248
1.250 0.6813 0.01819 0.00890 -0.1272 0.8303 0.1270
1.500 0.7119 0.01792 0.00859 -0.1275 0.8175 0.1292
1.750 0.7444 0.01769 0.00843 -0.1284 0.8057 0.1335
2.000 0.7787 0.01751 0.00824 -0.1295 0.7946 0.1372
2.250 0.8075 0.01740 0.00816 -0.1294 0.7816 0.1393
2.500 0.8380 0.01732 0.00810 -0.1297 0.7687 0.1418
2.750 0.8710 0.01716 0.00802 -0.1305 0.7529 0.1445
3.000 0.9017 0.01701 0.00787 -0.1305 0.7285 0.1496
3.250 0.9282 0.01694 0.00772 -0.1295 0.6951 0.1550
3.500 0.9546 0.01691 0.00765 -0.1286 0.6596 0.1585
3.750 0.9801 0.01697 0.00765 -0.1276 0.6155 0.1624
4.000 1.0041 0.01719 0.00769 -0.1263 0.5607 0.1674
4.250 1.0238 0.01774 0.00780 -0.1241 0.4732 0.1723
4.500 1.0395 0.01877 0.00821 -0.1216 0.3662 0.1802
4.750 1.0519 0.02036 0.00901 -0.1189 0.2212 0.1910
5.000 1.0620 0.02259 0.01024 -0.1162 0.0883 0.2028
5.250 1.0881 0.02347 0.01127 -0.1162 0.0750 0.2627
5.500 1.1409 0.02404 0.01277 -0.1225 0.0660 1.0000
5.750 1.1597 0.02503 0.01378 -0.1208 0.0613 1.0000
6.000 1.1768 0.02617 0.01493 -0.1188 0.0580 1.0000
6.250 1.1951 0.02717 0.01602 -0.1169 0.0557 1.0000
6.500 1.2129 0.02826 0.01716 -0.1150 0.0533 1.0000
6.750 1.2303 0.02942 0.01833 -0.1132 0.0506 1.0000
7.000 1.2469 0.03090 0.01973 -0.1113 0.0483 1.0000
7.250 1.2665 0.03234 0.02120 -0.1099 0.0467 1.0000
7.500 1.2882 0.03370 0.02265 -0.1087 0.0454 1.0000
7.750 1.3106 0.03520 0.02425 -0.1077 0.0440 1.0000
8.000 1.3326 0.03669 0.02587 -0.1067 0.0423 1.0000
8.250 1.3532 0.03816 0.02741 -0.1056 0.0404 1.0000
8.500 1.3741 0.03991 0.02918 -0.1048 0.0390 1.0000
8.750 1.3976 0.04253 0.03183 -0.1045 0.0379 1.0000
9.000 1.4163 0.04455 0.03421 -0.1029 0.0373 1.0000
9.250 1.4327 0.04680 0.03684 -0.1010 0.0365 1.0000
9.500 1.4459 0.04909 0.03951 -0.0988 0.0354 1.0000
9.750 1.4571 0.05138 0.04213 -0.0965 0.0342 1.0000
10.000 1.4665 0.05382 0.04486 -0.0941 0.0333 1.0000
10.250 1.4738 0.05646 0.04781 -0.0915 0.0325 1.0000
10.500 1.4783 0.05932 0.05096 -0.0887 0.0321 1.0000
10.750 1.4799 0.06226 0.05418 -0.0858 0.0318 1.0000
11.000 1.4790 0.06531 0.05748 -0.0827 0.0315 1.0000
11.250 1.4731 0.06849 0.06093 -0.0792 0.0313 1.0000
11.500 1.4619 0.07161 0.06428 -0.0752 0.0311 1.0000
11.750 1.4487 0.07490 0.06780 -0.0716 0.0309 1.0000
12.000 1.4352 0.07847 0.07157 -0.0688 0.0307 1.0000
12.250 1.4172 0.08259 0.07593 -0.0665 0.0306 1.0000
12.500 1.3988 0.08717 0.08073 -0.0652 0.0305 1.0000
12.750 1.3767 0.09237 0.08618 -0.0650 0.0305 1.0000
13.000 1.3486 0.09878 0.09289 -0.0661 0.0307 1.0000
13.250 1.3228 0.10573 0.10007 -0.0686 0.0307 1.0000
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Polar data table (+)
Polar graphs
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