Bergey BW-3 (smoothed) (bw3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Bergey BW-3 (smoothed) (bw3-il) Reynolds number: 500,000 Max Cl/Cd: 79.34 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bw3-il-500000-n5.txt Download as CSV file: xf-bw3-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3875 0.10068 0.09827 -0.0143 1.0000 0.0153
-7.750 -0.3885 0.09827 0.09589 -0.0137 1.0000 0.0151
-7.500 -0.3893 0.09556 0.09321 -0.0134 1.0000 0.0152
-7.250 -0.3712 0.09051 0.08815 -0.0192 0.9984 0.0155
-7.000 -0.3470 0.08599 0.08361 -0.0258 0.9963 0.0154
-6.750 -0.3222 0.07931 0.07690 -0.0351 0.9932 0.0160
-6.500 -0.2960 0.07743 0.07502 -0.0387 0.9904 0.0164
-6.000 -0.2713 0.07139 0.06900 -0.0422 0.9425 0.0168
-5.750 -0.2344 0.06632 0.06386 -0.0511 0.9337 0.0171
-5.500 -0.1924 0.06082 0.05828 -0.0612 0.9273 0.0174
-5.000 -0.0619 0.01612 0.01131 -0.1138 0.9155 0.0228
-4.750 -0.0214 0.01363 0.00841 -0.1174 0.9102 0.0237
-4.500 0.0225 0.01263 0.00722 -0.1213 0.9035 0.0249
-4.250 0.0693 0.01181 0.00622 -0.1259 0.8970 0.0266
-4.000 0.1149 0.01121 0.00543 -0.1301 0.8891 0.0282
-3.500 0.1908 0.01038 0.00434 -0.1347 0.8693 0.0322
-3.250 0.2230 0.01012 0.00393 -0.1356 0.8598 0.0342
-3.000 0.2523 0.00984 0.00359 -0.1358 0.8501 0.0377
-2.750 0.2811 0.00962 0.00330 -0.1359 0.8414 0.0418
-2.500 0.3092 0.00947 0.00311 -0.1358 0.8324 0.0469
-2.250 0.3371 0.00941 0.00304 -0.1356 0.8241 0.0529
-2.000 0.3647 0.00943 0.00304 -0.1353 0.8153 0.0587
-1.750 0.3921 0.00947 0.00304 -0.1350 0.8071 0.0632
-1.500 0.4193 0.00945 0.00297 -0.1346 0.7982 0.0666
-1.250 0.4460 0.00960 0.00311 -0.1341 0.7880 0.0693
-1.000 0.4722 0.00967 0.00313 -0.1335 0.7749 0.0719
-0.750 0.4982 0.00968 0.00305 -0.1328 0.7610 0.0744
-0.500 0.5245 0.00968 0.00299 -0.1322 0.7488 0.0767
-0.250 0.5509 0.00975 0.00306 -0.1317 0.7385 0.0789
0.000 0.5773 0.00980 0.00309 -0.1311 0.7285 0.0808
0.250 0.6039 0.00979 0.00307 -0.1306 0.7179 0.0828
0.500 0.6305 0.00975 0.00298 -0.1302 0.7082 0.0844
0.750 0.6571 0.00970 0.00289 -0.1297 0.6970 0.0858
1.000 0.6829 0.00971 0.00285 -0.1290 0.6813 0.0871
1.250 0.7083 0.00974 0.00280 -0.1282 0.6626 0.0879
1.500 0.7332 0.00970 0.00268 -0.1274 0.6351 0.0895
1.750 0.7579 0.00978 0.00268 -0.1265 0.6086 0.0909
2.000 0.7820 0.00992 0.00271 -0.1255 0.5756 0.0921
2.250 0.8053 0.01015 0.00277 -0.1244 0.5329 0.0934
2.500 0.8279 0.01045 0.00288 -0.1231 0.4823 0.0950
2.750 0.8495 0.01090 0.00306 -0.1217 0.4203 0.0969
3.000 0.8707 0.01142 0.00328 -0.1204 0.3556 0.0984
3.250 0.8917 0.01199 0.00354 -0.1190 0.2883 0.0996
3.500 0.9122 0.01262 0.00383 -0.1175 0.2164 0.1005
3.750 0.9247 0.01403 0.00451 -0.1147 0.0663 0.1012
4.000 0.9495 0.01430 0.00476 -0.1140 0.0529 0.1036
4.250 0.9744 0.01455 0.00502 -0.1134 0.0469 0.1054
4.500 0.9994 0.01478 0.00528 -0.1127 0.0434 0.1075
4.750 1.0237 0.01507 0.00559 -0.1120 0.0399 0.1101
5.000 1.0479 0.01537 0.00591 -0.1112 0.0372 0.1128
5.250 1.0726 0.01563 0.00621 -0.1105 0.0353 0.1153
5.500 1.0973 0.01592 0.00655 -0.1099 0.0335 0.1185
5.750 1.1212 0.01627 0.00693 -0.1091 0.0318 0.1219
6.000 1.1438 0.01672 0.00741 -0.1080 0.0301 0.1260
6.250 1.1677 0.01703 0.00779 -0.1072 0.0290 0.1304
6.500 1.1914 0.01738 0.00820 -0.1064 0.0278 0.1384
6.750 1.2151 0.01775 0.00864 -0.1057 0.0265 0.1554
7.250 1.3756 0.01920 0.01137 -0.1321 0.0231 1.0000
7.500 1.3970 0.01972 0.01192 -0.1309 0.0223 1.0000
7.750 1.4185 0.02019 0.01242 -0.1297 0.0214 1.0000
8.000 1.4388 0.02078 0.01304 -0.1283 0.0209 1.0000
8.250 1.4587 0.02138 0.01368 -0.1268 0.0203 1.0000
8.500 1.4770 0.02212 0.01445 -0.1251 0.0197 1.0000
8.750 1.4936 0.02301 0.01539 -0.1231 0.0192 1.0000
9.000 1.5116 0.02376 0.01622 -0.1213 0.0189 1.0000
9.250 1.5301 0.02444 0.01700 -0.1196 0.0183 1.0000
9.500 1.5475 0.02521 0.01784 -0.1178 0.0178 1.0000
9.750 1.5646 0.02597 0.01868 -0.1160 0.0173 1.0000
10.000 1.5814 0.02672 0.01949 -0.1142 0.0169 1.0000
10.250 1.5976 0.02747 0.02030 -0.1123 0.0164 1.0000
10.500 1.6116 0.02831 0.02122 -0.1100 0.0161 1.0000
10.750 1.6222 0.02919 0.02215 -0.1071 0.0158 1.0000
11.000 1.6296 0.03025 0.02329 -0.1036 0.0155 1.0000
11.250 1.6349 0.03159 0.02471 -0.1001 0.0153 1.0000
11.500 1.6426 0.03278 0.02602 -0.0969 0.0150 1.0000
11.750 1.6506 0.03399 0.02738 -0.0940 0.0148 1.0000
12.000 1.6580 0.03526 0.02879 -0.0912 0.0145 1.0000
12.250 1.6647 0.03663 0.03030 -0.0884 0.0143 1.0000
12.500 1.6701 0.03816 0.03197 -0.0856 0.0140 1.0000
12.750 1.6753 0.03974 0.03367 -0.0831 0.0137 1.0000
13.000 1.6808 0.04130 0.03534 -0.0809 0.0134 1.0000
13.250 1.6845 0.04314 0.03732 -0.0788 0.0132 1.0000
13.500 1.6880 0.04506 0.03936 -0.0769 0.0130 1.0000
13.750 1.6901 0.04722 0.04164 -0.0751 0.0128 1.0000
14.000 1.6920 0.04945 0.04399 -0.0736 0.0126 1.0000
14.250 1.6923 0.05195 0.04661 -0.0723 0.0125 1.0000
14.500 1.6908 0.05477 0.04956 -0.0710 0.0124 1.0000
14.750 1.6877 0.05787 0.05279 -0.0701 0.0122 1.0000
15.000 1.6830 0.06128 0.05633 -0.0694 0.0121 1.0000
15.250 1.6742 0.06536 0.06055 -0.0689 0.0119 1.0000
15.500 1.6635 0.06992 0.06527 -0.0687 0.0119 1.0000
15.750 1.6541 0.07448 0.07002 -0.0690 0.0118 1.0000
16.000 1.6419 0.07963 0.07539 -0.0697 0.0117 1.0000
16.250 1.6284 0.08527 0.08123 -0.0710 0.0116 1.0000
16.500 1.6116 0.09174 0.08790 -0.0729 0.0116 1.0000
16.750 1.5942 0.09865 0.09503 -0.0754 0.0115 1.0000
17.000 1.5734 0.10659 0.10316 -0.0788 0.0115 1.0000
17.250 1.5534 0.11480 0.11157 -0.0827 0.0115 1.0000
17.500 1.5278 0.12467 0.12165 -0.0880 0.0114 1.0000
17.750 1.5000 0.13543 0.13261 -0.0941 0.0115 1.0000
18.000 1.4675 0.14822 0.14561 -0.1018 0.0115 1.0000
18.250 1.3859 0.17722 0.17498 -0.1206 0.0117 1.0000
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