WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-140/35/FB 14% (wb140-il) Reynolds number: 500,000 Max Cl/Cd: 105.92 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb140-il-500000.txt Download as CSV file: xf-wb140-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WB-140/35/FB 14%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1010 0.08834 0.08542 -0.0908 0.8058 0.0240
-10.750 -0.1042 0.08388 0.08098 -0.0910 0.8037 0.0247
-10.500 -0.1851 0.09141 0.08841 -0.0872 0.8112 0.0240
-10.250 -0.1948 0.08354 0.08053 -0.0919 0.8083 0.0240
-9.750 -0.2305 0.06420 0.06111 -0.1092 0.8019 0.0240
-9.500 -0.2494 0.05518 0.05191 -0.1231 0.7980 0.0240
-9.250 -0.2578 0.05032 0.04677 -0.1280 0.7952 0.0240
-9.000 -0.2777 0.04119 0.03724 -0.1319 0.7929 0.0246
-8.750 -0.2641 0.03770 0.03377 -0.1326 0.7912 0.0251
-8.500 -0.2476 0.03538 0.03140 -0.1332 0.7893 0.0257
-8.250 -0.2301 0.03338 0.02930 -0.1338 0.7875 0.0267
-8.000 -0.2121 0.03145 0.02713 -0.1344 0.7856 0.0283
-7.750 -0.1980 0.02921 0.02422 -0.1348 0.7836 0.0315
-7.500 -0.1773 0.02641 0.02144 -0.1351 0.7819 0.0328
-7.250 -0.1547 0.02341 0.01751 -0.1339 0.7801 0.0244
-7.000 -0.1297 0.02189 0.01578 -0.1339 0.7785 0.0244
-6.750 -0.1053 0.01981 0.01354 -0.1339 0.7768 0.0247
-6.500 -0.0803 0.01830 0.01204 -0.1341 0.7747 0.0259
-6.250 -0.0538 0.01747 0.01118 -0.1343 0.7722 0.0273
-6.000 -0.0269 0.01660 0.01021 -0.1343 0.7697 0.0280
-5.750 0.0003 0.01583 0.00934 -0.1344 0.7674 0.0287
-5.500 0.0279 0.01519 0.00862 -0.1345 0.7655 0.0294
-5.250 0.0561 0.01481 0.00813 -0.1346 0.7637 0.0303
-5.000 0.0831 0.01398 0.00723 -0.1348 0.7620 0.0314
-4.750 0.1102 0.01325 0.00646 -0.1349 0.7601 0.0323
-4.500 0.1381 0.01276 0.00592 -0.1351 0.7578 0.0332
-4.250 0.1663 0.01236 0.00547 -0.1354 0.7552 0.0344
-4.000 0.1948 0.01205 0.00509 -0.1356 0.7525 0.0357
-3.750 0.2237 0.01182 0.00476 -0.1359 0.7501 0.0366
-3.500 0.2529 0.01167 0.00452 -0.1363 0.7481 0.0374
-3.250 0.2818 0.01153 0.00433 -0.1365 0.7459 0.0382
-3.000 0.3106 0.01141 0.00416 -0.1368 0.7430 0.0393
-2.750 0.3395 0.01133 0.00401 -0.1370 0.7396 0.0426
-2.500 0.3687 0.01128 0.00395 -0.1373 0.7367 0.0483
-2.250 0.3975 0.01111 0.00400 -0.1377 0.7342 0.1324
-2.000 0.4265 0.01111 0.00396 -0.1381 0.7319 0.1439
-1.750 0.4568 0.01166 0.00459 -0.1384 0.7292 0.1666
-1.500 0.4866 0.01216 0.00488 -0.1387 0.7261 0.1745
-1.250 0.5159 0.01237 0.00500 -0.1390 0.7232 0.1816
-1.000 0.5445 0.01222 0.00484 -0.1395 0.7205 0.1877
-0.750 0.5730 0.01206 0.00470 -0.1399 0.7176 0.1932
-0.500 0.6010 0.01201 0.00467 -0.1401 0.7150 0.1963
-0.250 0.6289 0.01189 0.00459 -0.1403 0.7119 0.1978
0.000 0.6566 0.01158 0.00438 -0.1406 0.7084 0.2021
0.250 0.6853 0.01152 0.00430 -0.1410 0.7050 0.2060
0.500 0.7134 0.01156 0.00434 -0.1411 0.7008 0.2063
0.750 0.7409 0.01152 0.00434 -0.1412 0.6959 0.2059
1.000 0.7696 0.01152 0.00432 -0.1414 0.6916 0.2055
1.250 0.7987 0.01159 0.00436 -0.1418 0.6884 0.2052
1.500 0.8259 0.01149 0.00435 -0.1418 0.6843 0.2050
1.750 0.8537 0.01143 0.00433 -0.1419 0.6802 0.2048
2.000 0.8821 0.01136 0.00429 -0.1422 0.6764 0.2046
2.250 0.9103 0.01129 0.00424 -0.1423 0.6726 0.2045
2.500 0.9371 0.01115 0.00420 -0.1423 0.6661 0.2043
2.750 0.9648 0.01101 0.00409 -0.1423 0.6605 0.2042
3.000 0.9920 0.01091 0.00408 -0.1424 0.6530 0.2041
3.250 1.0194 0.01079 0.00400 -0.1424 0.6458 0.2040
3.500 1.0465 0.01071 0.00397 -0.1423 0.6371 0.2040
3.750 1.0727 0.01062 0.00388 -0.1421 0.6276 0.2039
4.000 1.0980 0.01062 0.00385 -0.1417 0.6166 0.2039
4.250 1.1224 0.01071 0.00392 -0.1412 0.6027 0.2040
4.500 1.1461 0.01086 0.00404 -0.1406 0.5867 0.2040
4.750 1.1693 0.01104 0.00419 -0.1398 0.5689 0.2041
5.000 1.1912 0.01125 0.00437 -0.1389 0.5469 0.2042
5.250 1.2105 0.01157 0.00460 -0.1374 0.5236 0.2043
5.500 1.2286 0.01195 0.00489 -0.1358 0.5024 0.2044
5.750 1.2460 0.01235 0.00522 -0.1340 0.4803 0.2045
6.000 1.2604 0.01283 0.00561 -0.1317 0.4573 0.2047
6.250 1.2732 0.01332 0.00603 -0.1291 0.4374 0.2048
6.500 1.2832 0.01378 0.00644 -0.1260 0.4206 0.2049
6.750 1.2957 0.01428 0.00690 -0.1234 0.4038 0.2050
7.000 1.3103 0.01481 0.00740 -0.1214 0.3838 0.2052
7.500 1.3299 0.01636 0.00876 -0.1161 0.3323 0.2055
7.750 1.3384 0.01728 0.00959 -0.1134 0.3120 0.2057
8.000 1.3494 0.01811 0.01037 -0.1112 0.2940 0.2059
8.500 1.3712 0.01991 0.01208 -0.1070 0.2702 0.2064
8.750 1.3824 0.02084 0.01301 -0.1051 0.2611 0.2069
9.000 1.3954 0.02170 0.01389 -0.1035 0.2508 0.2074
9.250 1.4105 0.02245 0.01467 -0.1022 0.2378 0.2076
9.500 1.4213 0.02350 0.01565 -0.1005 0.2186 0.2078
9.750 1.4282 0.02484 0.01687 -0.0984 0.1951 0.2080
10.000 1.4299 0.02658 0.01844 -0.0959 0.1646 0.2081
10.250 1.4283 0.02861 0.02027 -0.0930 0.1351 0.2082
10.500 1.4116 0.03185 0.02310 -0.0889 0.0754 0.2082
10.750 1.3955 0.03525 0.02623 -0.0851 0.0280 0.2083
11.000 1.4002 0.03709 0.02808 -0.0834 0.0221 0.2084
11.250 1.4086 0.03867 0.02976 -0.0821 0.0204 0.2086
11.500 1.4150 0.04044 0.03162 -0.0807 0.0191 0.2089
11.750 1.4196 0.04240 0.03368 -0.0792 0.0178 0.2090
12.000 1.4224 0.04454 0.03595 -0.0776 0.0170 0.2093
12.250 1.4286 0.04639 0.03791 -0.0764 0.0165 0.2096
12.500 1.4331 0.04846 0.04007 -0.0751 0.0159 0.2098
12.750 1.4362 0.05070 0.04241 -0.0739 0.0153 0.2099
13.000 1.4372 0.05319 0.04500 -0.0727 0.0146 0.2102
13.250 1.4361 0.05597 0.04788 -0.0715 0.0141 0.2103
13.500 1.4320 0.05919 0.05120 -0.0703 0.0137 0.2106
13.750 1.4237 0.06299 0.05512 -0.0692 0.0134 0.2107
14.000 1.4106 0.06747 0.05973 -0.0681 0.0130 0.2107
14.250 1.4050 0.07120 0.06359 -0.0675 0.0128 0.2109
14.500 1.4055 0.07427 0.06677 -0.0672 0.0126 0.2112
14.750 1.4039 0.07767 0.07028 -0.0669 0.0124 0.2113
15.000 1.4013 0.08125 0.07397 -0.0667 0.0121 0.2116
15.250 1.3978 0.08498 0.07780 -0.0667 0.0119 0.2118
15.500 1.3942 0.08878 0.08171 -0.0667 0.0116 0.2121
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