Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 200,000 Max Cl/Cd: 74.66 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bw3-il-200000.txt Download as CSV file: xf-bw3-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3722 0.11339 0.10954 -0.0175 1.0000 0.0406
-8.250 -0.3786 0.11276 0.10898 -0.0186 1.0000 0.0408
-8.000 -0.3829 0.11164 0.10792 -0.0202 1.0000 0.0409
-7.750 -0.3702 0.10560 0.10188 -0.0177 1.0000 0.0413
-7.500 -0.3619 0.10201 0.09832 -0.0166 1.0000 0.0419
-7.250 -0.3577 0.09950 0.09584 -0.0158 1.0000 0.0426
-7.000 -0.3519 0.09699 0.09338 -0.0160 1.0000 0.0434
-6.750 -0.3455 0.09448 0.09091 -0.0165 1.0000 0.0449
-6.500 -0.3388 0.09203 0.08850 -0.0178 1.0000 0.0466
-6.250 -0.3268 0.09069 0.08720 -0.0245 1.0000 0.0480
-6.000 -0.3141 0.08936 0.08589 -0.0319 1.0000 0.0483
-5.750 -0.3194 0.08576 0.08237 -0.0268 1.0000 0.0486
-5.500 -0.3235 0.08323 0.07989 -0.0227 1.0000 0.0489
-5.250 -0.3178 0.08059 0.07728 -0.0215 0.9993 0.0494
-5.000 -0.2873 0.07688 0.07354 -0.0264 0.9963 0.0509
-4.750 -0.2510 0.07307 0.06969 -0.0335 0.9924 0.0532
-4.500 -0.1795 0.06804 0.06447 -0.0535 0.9876 0.0568
-4.250 -0.1634 0.06428 0.06074 -0.0526 0.9833 0.0578
-4.000 -0.1329 0.06105 0.05748 -0.0564 0.9785 0.0596
-3.750 -0.0909 0.05757 0.05393 -0.0634 0.9740 0.0629
-3.500 -0.0219 0.05303 0.04912 -0.0787 0.9678 0.0661
-3.250 0.0020 0.04953 0.04564 -0.0797 0.9643 0.0671
-3.000 0.0316 0.04691 0.04300 -0.0821 0.9576 0.0693
-2.750 0.1108 0.04449 0.04006 -0.0956 0.9543 0.0760
-2.500 0.1313 0.03998 0.03565 -0.0966 0.9485 0.0770
-2.250 0.1624 0.03735 0.03303 -0.0987 0.9444 0.0787
-2.000 0.2230 0.03583 0.03104 -0.1056 0.9418 0.0877
-1.750 0.2526 0.03178 0.02694 -0.1078 0.9360 0.0889
-1.500 0.2844 0.02952 0.02471 -0.1096 0.9320 0.0914
-1.250 0.3341 0.02740 0.02212 -0.1138 0.9292 0.1018
-1.000 0.3685 0.02510 0.01991 -0.1162 0.9261 0.1053
-0.750 0.4076 0.02339 0.01795 -0.1185 0.9198 0.1173
-0.500 0.4520 0.02173 0.01609 -0.1221 0.9159 0.1307
-0.250 0.5009 0.02016 0.01446 -0.1270 0.9123 0.1482
0.000 0.2553 0.01655 0.01279 -0.0537 0.9023 0.1463
0.250 0.5876 0.01811 0.01215 -0.1341 0.8935 0.2047
0.750 0.6617 0.01598 0.00933 -0.1362 0.8712 0.1604
1.000 0.6967 0.01542 0.00856 -0.1372 0.8609 0.1530
1.250 0.7247 0.01497 0.00800 -0.1369 0.8491 0.1503
1.500 0.7522 0.01474 0.00769 -0.1364 0.8375 0.1519
1.750 0.7810 0.01450 0.00737 -0.1361 0.8254 0.1529
2.000 0.8078 0.01424 0.00703 -0.1353 0.8096 0.1530
2.250 0.8327 0.01402 0.00675 -0.1340 0.7916 0.1539
2.500 0.8574 0.01385 0.00652 -0.1327 0.7732 0.1555
2.750 0.8820 0.01361 0.00627 -0.1314 0.7528 0.1585
3.000 0.9073 0.01340 0.00608 -0.1304 0.7323 0.1608
3.250 0.9320 0.01327 0.00593 -0.1292 0.7079 0.1632
3.500 0.9559 0.01320 0.00584 -0.1277 0.6794 0.1657
3.750 0.9793 0.01321 0.00578 -0.1263 0.6426 0.1688
4.000 1.0005 0.01340 0.00576 -0.1243 0.5835 0.1722
4.250 1.0159 0.01405 0.00588 -0.1213 0.4663 0.1772
4.500 1.0181 0.01602 0.00664 -0.1163 0.2574 0.1812
4.750 1.0254 0.01829 0.00784 -0.1128 0.0912 0.1853
5.000 1.0504 0.01903 0.00862 -0.1124 0.0786 0.1916
5.250 1.0722 0.02004 0.00964 -0.1112 0.0719 0.2008
5.500 1.0980 0.02074 0.01045 -0.1109 0.0677 0.2165
5.750 1.1829 0.02274 0.01342 -0.1254 0.0593 1.0000
6.000 1.2046 0.02365 0.01433 -0.1239 0.0578 1.0000
6.250 1.2264 0.02468 0.01537 -0.1225 0.0559 1.0000
6.500 1.2486 0.02575 0.01645 -0.1213 0.0537 1.0000
6.750 1.2709 0.02690 0.01762 -0.1202 0.0514 1.0000
7.000 1.2945 0.02836 0.01907 -0.1194 0.0501 1.0000
7.250 1.3199 0.03041 0.02111 -0.1190 0.0488 1.0000
7.500 1.3483 0.03392 0.02472 -0.1192 0.0477 1.0000
7.750 1.3679 0.03459 0.02564 -0.1173 0.0465 1.0000
8.000 1.3896 0.03627 0.02755 -0.1159 0.0457 1.0000
8.250 1.4107 0.03859 0.03013 -0.1145 0.0454 1.0000
8.500 1.4299 0.04127 0.03310 -0.1128 0.0453 1.0000
8.750 1.4467 0.04449 0.03666 -0.1108 0.0456 1.0000
9.000 1.4604 0.04784 0.04035 -0.1084 0.0459 1.0000
9.250 1.4707 0.05091 0.04377 -0.1056 0.0457 1.0000
12.750 1.1578 0.15279 0.14945 -0.1053 0.0666 1.0000
13.000 1.1526 0.15947 0.15611 -0.1088 0.0648 1.0000
13.250 1.1534 0.16404 0.16068 -0.1103 0.0630 1.0000
13.500 1.1592 0.16690 0.16354 -0.1101 0.0616 1.0000
13.750 1.1689 0.16839 0.16504 -0.1081 0.0605 1.0000
14.000 0.8812 0.16420 0.16102 -0.0889 0.0683 1.0000
14.250 0.8765 0.16826 0.16508 -0.0908 0.0656 1.0000
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Polar data table (+)
Polar graphs
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