Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 200,000 Max Cl/Cd: 68.53 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bw3-il-200000-n5.txt Download as CSV file: xf-bw3-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3607 0.10298 0.09920 -0.0166 1.0000 0.0317
-7.500 -0.3601 0.10071 0.09697 -0.0162 1.0000 0.0325
-7.250 -0.3611 0.09858 0.09491 -0.0181 1.0000 0.0341
-7.000 -0.3551 0.09590 0.09226 -0.0207 1.0000 0.0343
-6.750 -0.3472 0.09299 0.08939 -0.0243 1.0000 0.0344
-6.500 -0.3383 0.08991 0.08634 -0.0262 1.0000 0.0344
-6.250 -0.3282 0.08650 0.08297 -0.0272 0.9996 0.0345
-6.000 -0.2954 0.08181 0.07822 -0.0355 0.9965 0.0344
-5.250 -0.2150 0.06742 0.06371 -0.0503 0.9813 0.0283
-5.000 -0.1963 0.06518 0.06150 -0.0517 0.9631 0.0298
-4.750 -0.1675 0.06192 0.05820 -0.0563 0.9507 0.0307
-4.500 -0.1281 0.05674 0.05291 -0.0647 0.9429 0.0301
-4.250 -0.0844 0.05113 0.04715 -0.0738 0.9365 0.0296
-4.000 -0.0430 0.04700 0.04289 -0.0807 0.9311 0.0300
-3.750 -0.0003 0.04329 0.03906 -0.0872 0.9268 0.0312
-3.500 0.0482 0.03779 0.03331 -0.0956 0.9215 0.0334
-3.250 0.0982 0.03091 0.02601 -0.1040 0.9171 0.0349
-2.750 0.1830 0.02222 0.01649 -0.1133 0.9077 0.0418
-2.500 0.2213 0.01766 0.01122 -0.1163 0.9026 0.0477
-2.250 0.2661 0.01831 0.01197 -0.1200 0.8976 0.0501
-2.000 0.3068 0.01610 0.00929 -0.1230 0.8918 0.0573
-1.500 0.3900 0.01553 0.00846 -0.1291 0.8774 0.0674
-1.250 0.4257 0.01560 0.00849 -0.1308 0.8680 0.0718
-1.000 0.4606 0.01507 0.00774 -0.1323 0.8594 0.0778
-0.750 0.4918 0.01516 0.00782 -0.1330 0.8494 0.0813
-0.500 0.5216 0.01475 0.00715 -0.1331 0.8397 0.0872
-0.250 0.5516 0.01448 0.00680 -0.1335 0.8291 0.0898
0.000 0.5779 0.01437 0.00667 -0.1329 0.8156 0.0923
0.250 0.6045 0.01421 0.00643 -0.1324 0.8024 0.0956
0.500 0.6319 0.01395 0.00604 -0.1320 0.7906 0.0981
0.750 0.6592 0.01379 0.00574 -0.1316 0.7798 0.1007
1.000 0.6855 0.01354 0.00550 -0.1311 0.7687 0.1028
1.250 0.7127 0.01339 0.00534 -0.1307 0.7585 0.1045
1.500 0.7394 0.01326 0.00521 -0.1303 0.7473 0.1061
1.750 0.7659 0.01315 0.00510 -0.1297 0.7351 0.1081
2.000 0.7916 0.01308 0.00500 -0.1289 0.7177 0.1105
2.250 0.8166 0.01307 0.00489 -0.1279 0.6953 0.1132
2.500 0.8408 0.01307 0.00482 -0.1268 0.6684 0.1148
2.750 0.8655 0.01303 0.00474 -0.1258 0.6377 0.1166
3.000 0.8891 0.01311 0.00474 -0.1246 0.6010 0.1184
3.250 0.9121 0.01331 0.00479 -0.1233 0.5562 0.1207
3.500 0.9324 0.01373 0.00491 -0.1215 0.4865 0.1228
3.750 0.9513 0.01435 0.00517 -0.1196 0.4112 0.1258
4.000 0.9686 0.01523 0.00558 -0.1176 0.3228 0.1287
4.250 0.9853 0.01641 0.00617 -0.1158 0.2022 0.1315
4.500 0.9983 0.01813 0.00711 -0.1134 0.0711 0.1340
4.750 1.0229 0.01868 0.00764 -0.1128 0.0605 0.1379
5.000 1.0482 0.01913 0.00816 -0.1123 0.0548 0.1417
5.250 1.0740 0.01967 0.00875 -0.1121 0.0502 0.1470
5.500 1.0972 0.02035 0.00949 -0.1112 0.0471 0.1539
5.750 1.1223 0.02089 0.01015 -0.1108 0.0447 0.1660
6.000 1.1483 0.02148 0.01087 -0.1107 0.0418 0.2021
6.500 1.2528 0.02343 0.01391 -0.1237 0.0366 1.0000
6.750 1.2724 0.02428 0.01481 -0.1221 0.0352 1.0000
7.000 1.2917 0.02516 0.01572 -0.1205 0.0339 1.0000
7.250 1.3112 0.02599 0.01657 -0.1190 0.0324 1.0000
7.500 1.3296 0.02694 0.01752 -0.1174 0.0312 1.0000
7.750 1.3463 0.02839 0.01897 -0.1156 0.0303 1.0000
8.000 1.3659 0.02944 0.02012 -0.1141 0.0297 1.0000
8.250 1.3853 0.03062 0.02142 -0.1126 0.0289 1.0000
8.500 1.4045 0.03178 0.02270 -0.1111 0.0279 1.0000
8.750 1.4231 0.03288 0.02393 -0.1096 0.0268 1.0000
9.000 1.4410 0.03401 0.02515 -0.1081 0.0260 1.0000
9.250 1.4582 0.03516 0.02636 -0.1065 0.0253 1.0000
9.500 1.4750 0.03657 0.02782 -0.1049 0.0247 1.0000
9.750 1.4919 0.03850 0.02987 -0.1035 0.0241 1.0000
10.000 1.5071 0.04035 0.03200 -0.1015 0.0237 1.0000
10.250 1.5198 0.04242 0.03440 -0.0993 0.0230 1.0000
10.500 1.5306 0.04449 0.03675 -0.0969 0.0223 1.0000
10.750 1.5396 0.04646 0.03896 -0.0943 0.0216 1.0000
11.000 1.5469 0.04821 0.04089 -0.0916 0.0210 1.0000
11.250 1.5491 0.05026 0.04317 -0.0882 0.0207 1.0000
11.500 1.5483 0.05220 0.04530 -0.0845 0.0204 1.0000
11.750 1.5462 0.05430 0.04757 -0.0809 0.0201 1.0000
12.000 1.5431 0.05646 0.04990 -0.0776 0.0199 1.0000
12.250 1.5375 0.05909 0.05272 -0.0744 0.0197 1.0000
12.500 1.5310 0.06187 0.05567 -0.0718 0.0195 1.0000
12.750 1.5215 0.06524 0.05924 -0.0695 0.0194 1.0000
13.000 1.5087 0.06925 0.06348 -0.0676 0.0193 1.0000
13.250 1.4896 0.07412 0.06864 -0.0663 0.0192 1.0000
13.500 1.4655 0.08010 0.07495 -0.0659 0.0191 1.0000
13.750 1.4425 0.08635 0.08146 -0.0666 0.0191 1.0000
14.000 1.4174 0.09347 0.08884 -0.0685 0.0190 1.0000
14.250 1.3924 0.10112 0.09674 -0.0715 0.0191 1.0000
14.500 1.3687 0.10930 0.10512 -0.0755 0.0191 1.0000
14.750 1.3411 0.11927 0.11529 -0.0813 0.0191 1.0000
15.000 1.3148 0.13011 0.12631 -0.0883 0.0192 1.0000
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Polar data table (+)
Polar graphs
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