Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.64 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bw3-il-1000000.txt Download as CSV file: xf-bw3-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4080 0.11124 0.10950 -0.0115 1.0000 0.0162
-8.750 -0.4019 0.10888 0.10716 -0.0117 1.0000 0.0163
-8.500 -0.3964 0.10660 0.10489 -0.0118 1.0000 0.0165
-8.250 -0.3916 0.10434 0.10265 -0.0119 1.0000 0.0167
-8.000 -0.3882 0.10207 0.10039 -0.0118 1.0000 0.0170
-7.750 -0.2759 0.08102 0.07947 -0.0256 0.9981 0.0195
-7.500 -0.2652 0.07646 0.07491 -0.0295 0.9965 0.0195
-7.250 -0.2546 0.07153 0.06998 -0.0320 0.9950 0.0199
-7.000 -0.2406 0.06795 0.06640 -0.0350 0.9918 0.0201
-6.750 -0.2189 0.06436 0.06280 -0.0393 0.9895 0.0204
-6.500 -0.2179 0.06236 0.06083 -0.0382 0.9683 0.0209
-6.250 -0.2015 0.05859 0.05703 -0.0418 0.9395 0.0214
-6.000 -0.1735 0.05355 0.05196 -0.0490 0.9334 0.0226
-5.500 -0.1575 0.01671 0.01318 -0.1044 0.9439 0.0217
-5.250 -0.1267 0.01355 0.00966 -0.1061 0.9376 0.0224
-5.000 -0.0889 0.01227 0.00816 -0.1085 0.9321 0.0231
-4.500 -0.0044 0.01005 0.00550 -0.1153 0.9216 0.0250
-4.250 0.0433 0.00941 0.00474 -0.1199 0.9159 0.0262
-4.000 0.0922 0.00892 0.00412 -0.1247 0.9084 0.0278
-3.750 0.1418 0.00847 0.00350 -0.1298 0.9002 0.0294
-3.500 0.1888 0.00812 0.00307 -0.1343 0.8907 0.0324
-3.000 0.2568 0.00771 0.00248 -0.1369 0.8680 0.0380
-2.750 0.2860 0.00758 0.00227 -0.1370 0.8580 0.0415
-2.500 0.3142 0.00745 0.00211 -0.1369 0.8481 0.0478
-2.250 0.3415 0.00741 0.00208 -0.1366 0.8388 0.0564
-2.000 0.3690 0.00754 0.00221 -0.1363 0.8282 0.0630
-1.750 0.3951 0.00762 0.00224 -0.1356 0.8160 0.0661
-1.500 0.4215 0.00775 0.00238 -0.1350 0.8044 0.0697
-1.250 0.4483 0.00795 0.00255 -0.1345 0.7945 0.0723
-1.000 0.4750 0.00805 0.00264 -0.1339 0.7853 0.0745
-0.750 0.5018 0.00823 0.00278 -0.1334 0.7764 0.0758
-0.500 0.5283 0.00802 0.00255 -0.1330 0.7671 0.0787
-0.250 0.5550 0.00809 0.00260 -0.1325 0.7585 0.0803
0.000 0.5816 0.00816 0.00268 -0.1320 0.7492 0.0822
0.250 0.6081 0.00828 0.00278 -0.1315 0.7395 0.0847
0.500 0.6341 0.00833 0.00277 -0.1308 0.7275 0.0862
0.750 0.6599 0.00838 0.00278 -0.1301 0.7131 0.0873
1.000 0.6858 0.00826 0.00259 -0.1295 0.6967 0.0886
1.250 0.7119 0.00808 0.00236 -0.1289 0.6797 0.0904
1.750 0.7636 0.00815 0.00235 -0.1277 0.6427 0.0933
2.000 0.7889 0.00822 0.00234 -0.1269 0.6156 0.0946
2.250 0.8142 0.00831 0.00234 -0.1262 0.5877 0.0958
2.500 0.8384 0.00850 0.00238 -0.1253 0.5476 0.0974
2.750 0.8616 0.00882 0.00248 -0.1242 0.4917 0.0988
3.000 0.8822 0.00940 0.00268 -0.1226 0.4054 0.0998
3.250 0.9025 0.01004 0.00294 -0.1211 0.3251 0.1007
3.500 0.9218 0.01073 0.00321 -0.1194 0.2347 0.1019
3.750 0.9330 0.01218 0.00386 -0.1161 0.0641 0.1039
4.000 0.9575 0.01245 0.00408 -0.1154 0.0511 0.1058
4.250 0.9827 0.01265 0.00430 -0.1147 0.0460 0.1073
4.500 1.0078 0.01287 0.00452 -0.1140 0.0426 0.1094
4.750 1.0315 0.01322 0.00489 -0.1131 0.0383 0.1117
5.000 1.0567 0.01342 0.00512 -0.1124 0.0371 0.1137
5.250 1.0819 0.01362 0.00534 -0.1118 0.0354 0.1156
5.500 1.1074 0.01385 0.00559 -0.1114 0.0335 0.1193
5.750 1.1306 0.01424 0.00601 -0.1104 0.0312 0.1229
6.000 1.1538 0.01463 0.00645 -0.1094 0.0299 0.1265
6.250 1.1785 0.01489 0.00675 -0.1087 0.0289 0.1305
6.500 1.2030 0.01519 0.00711 -0.1080 0.0279 0.1382
6.750 1.2275 0.01550 0.00746 -0.1074 0.0268 0.1527
7.000 1.3809 0.01652 0.00981 -0.1388 0.0237 1.0000
7.250 1.4035 0.01694 0.01026 -0.1377 0.0231 1.0000
7.500 1.4256 0.01739 0.01073 -0.1366 0.0224 1.0000
7.750 1.4476 0.01783 0.01120 -0.1354 0.0218 1.0000
8.000 1.4698 0.01823 0.01162 -0.1343 0.0211 1.0000
8.250 1.4906 0.01876 0.01215 -0.1330 0.0205 1.0000
8.500 1.5076 0.01965 0.01308 -0.1309 0.0197 1.0000
8.750 1.5227 0.02075 0.01426 -0.1285 0.0191 1.0000
9.000 1.5423 0.02135 0.01493 -0.1270 0.0189 1.0000
9.250 1.5626 0.02187 0.01549 -0.1256 0.0185 1.0000
9.500 1.5815 0.02252 0.01619 -0.1240 0.0181 1.0000
9.750 1.5998 0.02320 0.01694 -0.1223 0.0177 1.0000
10.000 1.6178 0.02390 0.01769 -0.1206 0.0173 1.0000
10.250 1.6379 0.02429 0.01811 -0.1193 0.0167 1.0000
10.500 1.6550 0.02498 0.01883 -0.1175 0.0164 1.0000
10.750 1.6706 0.02576 0.01965 -0.1154 0.0160 1.0000
11.000 1.6785 0.02733 0.02131 -0.1121 0.0154 1.0000
11.250 1.6823 0.02906 0.02318 -0.1081 0.0152 1.0000
11.500 1.6919 0.02973 0.02393 -0.1048 0.0150 1.0000
11.750 1.7005 0.03060 0.02490 -0.1016 0.0148 1.0000
12.000 1.7091 0.03150 0.02589 -0.0985 0.0146 1.0000
12.250 1.7160 0.03268 0.02717 -0.0954 0.0144 1.0000
12.500 1.7223 0.03390 0.02850 -0.0922 0.0141 1.0000
12.750 1.7281 0.03523 0.02994 -0.0892 0.0139 1.0000
13.000 1.7333 0.03662 0.03144 -0.0864 0.0137 1.0000
13.250 1.7386 0.03801 0.03293 -0.0837 0.0135 1.0000
13.500 1.7432 0.03954 0.03456 -0.0813 0.0132 1.0000
13.750 1.7460 0.04137 0.03648 -0.0790 0.0131 1.0000
14.000 1.7503 0.04307 0.03826 -0.0772 0.0129 1.0000
14.250 1.7530 0.04504 0.04032 -0.0754 0.0127 1.0000
14.500 1.7530 0.04743 0.04281 -0.0737 0.0126 1.0000
14.750 1.7523 0.04994 0.04541 -0.0723 0.0124 1.0000
15.000 1.7454 0.05335 0.04896 -0.0708 0.0122 1.0000
15.250 1.7280 0.05826 0.05408 -0.0692 0.0120 1.0000
15.750 1.6960 0.06839 0.06463 -0.0681 0.0118 1.0000
16.000 1.6890 0.07251 0.06889 -0.0684 0.0118 1.0000
16.250 1.6801 0.07708 0.07360 -0.0690 0.0117 1.0000
16.500 1.6666 0.08258 0.07926 -0.0701 0.0117 1.0000
16.750 1.6526 0.08847 0.08532 -0.0718 0.0116 1.0000
17.000 1.6317 0.09582 0.09285 -0.0743 0.0116 1.0000
17.250 1.6193 0.10204 0.09921 -0.0769 0.0115 1.0000
17.500 1.5950 0.11085 0.10821 -0.0810 0.0115 1.0000
17.750 1.5649 0.12129 0.11885 -0.0863 0.0116 1.0000
18.000 1.5413 0.13088 0.12861 -0.0917 0.0115 1.0000
18.250 1.5036 0.14439 0.14234 -0.0998 0.0116 1.0000
18.500 1.4425 0.16570 0.16393 -0.1136 0.0117 1.0000
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