WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-140/35/FB 14% (wb140-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.31 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb140-il-1000000.txt Download as CSV file: xf-wb140-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1240 0.08763 0.08497 -0.0858 0.7422 0.0150
-11.000 -0.4302 0.04725 0.04425 -0.1106 0.7452 0.0106
-10.750 -0.4530 0.03628 0.03292 -0.1261 0.7443 0.0106
-10.500 -0.4609 0.03092 0.02714 -0.1284 0.7435 0.0108
-10.250 -0.4519 0.02792 0.02382 -0.1289 0.7427 0.0110
-10.000 -0.4468 0.02385 0.01932 -0.1290 0.7419 0.0114
-9.750 -0.4240 0.02303 0.01841 -0.1292 0.7412 0.0116
-9.500 -0.3993 0.02253 0.01785 -0.1294 0.7405 0.0118
-9.250 -0.3743 0.02204 0.01729 -0.1297 0.7398 0.0120
-9.000 -0.3495 0.02144 0.01659 -0.1298 0.7388 0.0123
-8.750 -0.3243 0.02087 0.01593 -0.1300 0.7375 0.0128
-8.500 -0.2995 0.02010 0.01501 -0.1301 0.7359 0.0134
-8.250 -0.2743 0.01929 0.01403 -0.1301 0.7341 0.0140
-8.000 -0.2479 0.01876 0.01335 -0.1303 0.7325 0.0144
-7.750 -0.2252 0.01700 0.01144 -0.1302 0.7317 0.0150
-7.500 -0.1987 0.01644 0.01085 -0.1305 0.7308 0.0154
-7.250 -0.1715 0.01604 0.01041 -0.1307 0.7298 0.0159
-7.000 -0.1441 0.01561 0.00994 -0.1310 0.7289 0.0165
-6.750 -0.1166 0.01515 0.00942 -0.1312 0.7278 0.0172
-6.500 -0.0887 0.01476 0.00895 -0.1314 0.7267 0.0180
-6.250 -0.0597 0.01473 0.00883 -0.1317 0.7257 0.0186
-6.000 -0.0344 0.01349 0.00756 -0.1318 0.7248 0.0198
-5.750 -0.0067 0.01307 0.00712 -0.1321 0.7237 0.0206
-5.500 0.0213 0.01271 0.00674 -0.1324 0.7222 0.0214
-5.250 0.0495 0.01241 0.00638 -0.1326 0.7204 0.0222
-5.000 0.0780 0.01219 0.00610 -0.1329 0.7183 0.0230
-4.750 0.1069 0.01202 0.00590 -0.1333 0.7172 0.0236
-4.500 0.1356 0.01171 0.00556 -0.1336 0.7163 0.0243
-4.250 0.1634 0.01105 0.00484 -0.1339 0.7152 0.0253
-4.000 0.1921 0.01071 0.00448 -0.1342 0.7139 0.0261
-3.750 0.2210 0.01047 0.00422 -0.1346 0.7123 0.0271
-3.500 0.2501 0.01029 0.00399 -0.1349 0.7102 0.0280
-3.250 0.2791 0.01015 0.00380 -0.1352 0.7078 0.0285
-3.000 0.3083 0.01007 0.00366 -0.1356 0.7056 0.0291
-2.750 0.3375 0.01006 0.00360 -0.1360 0.7036 0.0296
-2.500 0.3668 0.00995 0.00348 -0.1364 0.7023 0.0302
-2.250 0.3960 0.00981 0.00334 -0.1367 0.7008 0.0310
-2.000 0.4251 0.00969 0.00320 -0.1371 0.6988 0.0331
-1.750 0.4544 0.00959 0.00310 -0.1374 0.6965 0.0361
-1.500 0.4833 0.00937 0.00307 -0.1378 0.6943 0.0971
-1.250 0.5120 0.00921 0.00300 -0.1382 0.6921 0.1351
-1.000 0.5413 0.00919 0.00294 -0.1386 0.6895 0.1434
-0.750 0.5707 0.00918 0.00294 -0.1389 0.6869 0.1492
-0.500 0.6012 0.00959 0.00345 -0.1392 0.6836 0.1657
-0.250 0.6305 0.00964 0.00347 -0.1396 0.6804 0.1689
0.000 0.6599 0.00968 0.00348 -0.1399 0.6777 0.1714
0.250 0.6891 0.00971 0.00349 -0.1403 0.6753 0.1733
0.500 0.7184 0.00979 0.00354 -0.1407 0.6727 0.1745
0.750 0.7472 0.00962 0.00344 -0.1410 0.6694 0.1769
1.000 0.7762 0.00950 0.00337 -0.1414 0.6653 0.1784
1.250 0.8050 0.00938 0.00327 -0.1418 0.6611 0.1781
1.500 0.8339 0.00927 0.00320 -0.1421 0.6547 0.1777
1.750 0.8623 0.00915 0.00308 -0.1424 0.6455 0.1774
2.000 0.8902 0.00906 0.00298 -0.1425 0.6336 0.1772
2.250 0.9171 0.00906 0.00293 -0.1425 0.6216 0.1770
2.500 0.9436 0.00912 0.00296 -0.1424 0.6103 0.1768
2.750 0.9697 0.00922 0.00301 -0.1422 0.5992 0.1766
3.000 0.9966 0.00929 0.00308 -0.1422 0.5873 0.1764
3.250 1.0228 0.00940 0.00316 -0.1421 0.5725 0.1763
3.500 1.0472 0.00958 0.00327 -0.1417 0.5496 0.1762
3.750 1.0689 0.00990 0.00345 -0.1407 0.5191 0.1761
4.000 1.0907 0.01021 0.00365 -0.1398 0.4922 0.1760
4.250 1.1128 0.01050 0.00387 -0.1389 0.4704 0.1760
4.500 1.1353 0.01076 0.00406 -0.1382 0.4521 0.1760
4.750 1.1577 0.01101 0.00426 -0.1374 0.4377 0.1760
5.000 1.1799 0.01125 0.00447 -0.1366 0.4244 0.1761
5.250 1.2011 0.01151 0.00470 -0.1356 0.4090 0.1762
5.500 1.2217 0.01179 0.00493 -0.1344 0.3916 0.1763
5.750 1.2405 0.01211 0.00519 -0.1330 0.3675 0.1765
6.000 1.2539 0.01260 0.00554 -0.1306 0.3377 0.1766
6.250 1.2624 0.01305 0.00591 -0.1271 0.3157 0.1768
6.500 1.2737 0.01357 0.00634 -0.1243 0.2935 0.1770
6.750 1.2881 0.01411 0.00681 -0.1222 0.2782 0.1773
7.000 1.3046 0.01458 0.00726 -0.1206 0.2701 0.1776
7.250 1.3211 0.01506 0.00774 -0.1190 0.2617 0.1780
7.500 1.3400 0.01544 0.00815 -0.1179 0.2550 0.1784
7.750 1.3559 0.01598 0.00868 -0.1163 0.2463 0.1789
8.000 1.3740 0.01642 0.00911 -0.1151 0.2336 0.1793
8.250 1.3875 0.01711 0.00972 -0.1132 0.2155 0.1799
8.500 1.3993 0.01792 0.01046 -0.1112 0.1982 0.1803
8.750 1.4050 0.01910 0.01148 -0.1083 0.1712 0.1808
9.000 1.4076 0.02052 0.01273 -0.1053 0.1444 0.1811
9.250 1.4093 0.02208 0.01412 -0.1022 0.1147 0.1815
9.750 1.3840 0.02744 0.01892 -0.0932 0.0204 0.1819
10.000 1.3955 0.02855 0.02008 -0.0918 0.0170 0.1827
10.250 1.4093 0.02950 0.02113 -0.0908 0.0160 0.1836
10.500 1.4211 0.03062 0.02232 -0.0895 0.0150 0.1845
10.750 1.4311 0.03191 0.02369 -0.0881 0.0140 0.1855
11.000 1.4381 0.03349 0.02535 -0.0865 0.0129 0.1866
11.250 1.4506 0.03464 0.02656 -0.0855 0.0125 0.1872
11.500 1.4617 0.03593 0.02791 -0.0844 0.0119 0.1880
11.750 1.4716 0.03735 0.02939 -0.0833 0.0113 0.1885
12.000 1.4805 0.03888 0.03097 -0.0821 0.0109 0.1895
12.250 1.4884 0.04053 0.03270 -0.0810 0.0104 0.1902
12.500 1.4906 0.04272 0.03498 -0.0794 0.0099 0.1907
12.750 1.4926 0.04492 0.03729 -0.0779 0.0095 0.1911
13.000 1.5012 0.04657 0.03902 -0.0770 0.0093 0.1922
13.250 1.5088 0.04833 0.04085 -0.0761 0.0090 0.1927
13.500 1.5153 0.05022 0.04282 -0.0751 0.0087 0.1935
13.750 1.5211 0.05222 0.04488 -0.0742 0.0083 0.1940
14.000 1.5262 0.05430 0.04703 -0.0734 0.0080 0.1945
14.250 1.5304 0.05652 0.04932 -0.0725 0.0077 0.1949
14.500 1.5311 0.05920 0.05208 -0.0716 0.0075 0.1955
14.750 1.5264 0.06257 0.05554 -0.0707 0.0073 0.1955
15.000 1.5122 0.06715 0.06026 -0.0696 0.0070 0.1958
15.250 1.5090 0.07056 0.06377 -0.0691 0.0069 0.1960
15.500 1.5107 0.07343 0.06673 -0.0688 0.0068 0.1963
15.750 1.5101 0.07664 0.07003 -0.0686 0.0067 0.1966
16.000 1.5083 0.08006 0.07355 -0.0685 0.0065 0.1967
16.250 1.5051 0.08371 0.07730 -0.0685 0.0064 0.1969
16.500 1.5005 0.08761 0.08130 -0.0686 0.0062 0.1971
16.750 1.4955 0.09165 0.08543 -0.0689 0.0061 0.1972
17.000 1.4906 0.09572 0.08960 -0.0693 0.0060 0.1974
17.250 1.4846 0.10002 0.09400 -0.0699 0.0059 0.1976
17.500 1.4786 0.10434 0.09840 -0.0706 0.0058 0.1977
17.750 1.4722 0.10875 0.10291 -0.0714 0.0057 0.1977
18.000 1.4659 0.11321 0.10746 -0.0724 0.0056 0.1979
18.250 1.4599 0.11768 0.11201 -0.0735 0.0055 0.1980
18.500 1.4533 0.12227 0.11669 -0.0748 0.0054 0.1981
18.750 1.4467 0.12689 0.12139 -0.0762 0.0053 0.1982
19.000 1.4399 0.13153 0.12612 -0.0777 0.0052 0.1983
19.250 1.4329 0.13623 0.13089 -0.0793 0.0051 0.1983
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Polar data table (+)
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