WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WB-140/35/FB 14% (wb140-il) Reynolds number: 100,000 Max Cl/Cd: 52.9 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb140-il-100000-n5.txt Download as CSV file: xf-wb140-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3853 0.09857 0.09388 -0.0548 1.0000 0.0347
-10.750 -0.4811 0.07549 0.07093 -0.0675 0.9994 0.0306
-10.500 -0.4967 0.06469 0.05996 -0.0808 0.9856 0.0302
-10.250 -0.5125 0.05747 0.05240 -0.0886 0.9699 0.0301
-10.000 -0.5212 0.05219 0.04661 -0.0921 0.9562 0.0304
-9.750 -0.5222 0.04754 0.04162 -0.0933 0.9449 0.0312
-9.500 -0.5105 0.04399 0.03784 -0.0945 0.9377 0.0322
-9.250 -0.5009 0.04119 0.03473 -0.0942 0.9278 0.0329
-9.000 -0.4849 0.03846 0.03165 -0.0946 0.9212 0.0337
-8.750 -0.4692 0.03620 0.02906 -0.0942 0.9133 0.0345
-8.500 -0.4504 0.03427 0.02679 -0.0940 0.9060 0.0361
-8.250 -0.4279 0.03250 0.02465 -0.0941 0.9009 0.0381
-8.000 -0.4089 0.03111 0.02294 -0.0933 0.8930 0.0392
-7.750 -0.3856 0.02955 0.02113 -0.0931 0.8879 0.0400
-7.500 -0.3619 0.02782 0.01926 -0.0931 0.8843 0.0415
-7.250 -0.3419 0.02678 0.01813 -0.0925 0.8782 0.0437
-7.000 -0.3185 0.02585 0.01705 -0.0922 0.8735 0.0458
-6.750 -0.2930 0.02498 0.01595 -0.0921 0.8698 0.0472
-6.500 -0.2665 0.02422 0.01499 -0.0921 0.8666 0.0485
-6.250 -0.2435 0.02369 0.01430 -0.0916 0.8616 0.0501
-6.000 -0.2192 0.02304 0.01356 -0.0914 0.8577 0.0532
-5.750 -0.1930 0.02250 0.01293 -0.0914 0.8545 0.0564
-5.500 -0.1655 0.02204 0.01236 -0.0916 0.8519 0.0593
-5.250 -0.1373 0.02161 0.01185 -0.0918 0.8497 0.0639
-5.000 -0.1137 0.02133 0.01167 -0.0914 0.8454 0.0759
-4.750 -0.0880 0.02134 0.01190 -0.0914 0.8416 0.1141
-4.500 -0.0603 0.02125 0.01140 -0.0914 0.8383 0.1472
-4.250 -0.0319 0.02143 0.01166 -0.0916 0.8355 0.1577
-4.000 -0.0020 0.02416 0.01337 -0.0911 0.8330 0.1751
-3.750 0.0221 0.02424 0.01312 -0.0908 0.8295 0.1781
-3.500 0.0466 0.02369 0.01248 -0.0908 0.8259 0.1842
-3.250 0.0729 0.02290 0.01169 -0.0910 0.8228 0.1909
-3.000 0.1003 0.02198 0.01082 -0.0914 0.8199 0.1994
-2.750 0.1291 0.02119 0.01017 -0.0918 0.8171 0.2034
-2.500 0.1565 0.02075 0.00974 -0.0920 0.8138 0.2077
-2.250 0.1768 0.02014 0.00943 -0.0911 0.8081 0.2140
-2.000 0.2004 0.01943 0.00902 -0.0908 0.8032 0.2244
-1.750 0.2287 0.01898 0.00878 -0.0910 0.7991 0.2370
-1.250 0.2784 0.01899 0.00872 -0.0901 0.7866 0.2488
-1.000 0.3081 0.01885 0.00849 -0.0903 0.7824 0.2537
-0.750 0.3317 0.01894 0.00857 -0.0898 0.7759 0.2577
-0.500 0.3581 0.01892 0.00854 -0.0896 0.7704 0.2620
-0.250 0.3876 0.01881 0.00839 -0.0898 0.7666 0.2668
0.000 0.4124 0.01891 0.00850 -0.0895 0.7613 0.2716
0.250 0.4385 0.01895 0.00856 -0.0894 0.7561 0.2780
0.500 0.4676 0.01885 0.00848 -0.0896 0.7522 0.2868
0.750 0.4949 0.01882 0.00851 -0.0896 0.7477 0.3036
1.000 0.5192 0.01857 0.00869 -0.0893 0.7423 0.4244
1.250 0.5464 0.01828 0.00872 -0.0893 0.7383 0.5131
1.500 0.5759 0.01805 0.00865 -0.0895 0.7351 0.5736
1.750 0.5944 0.01786 0.00901 -0.0875 0.7282 0.7129
2.000 0.6236 0.01755 0.00898 -0.0870 0.7225 0.8304
2.250 0.6568 0.01754 0.00905 -0.0878 0.7144 0.8851
2.500 0.6921 0.01747 0.00896 -0.0890 0.7071 0.9285
2.750 0.7181 0.01768 0.00923 -0.0889 0.6978 0.9559
3.000 0.7479 0.01775 0.00929 -0.0893 0.6896 0.9761
3.250 0.7727 0.01791 0.00951 -0.0890 0.6787 0.9985
3.500 0.7894 0.01817 0.00989 -0.0872 0.6660 1.0000
3.750 0.8054 0.01845 0.01026 -0.0853 0.6525 1.0000
4.000 0.8238 0.01863 0.01052 -0.0838 0.6396 1.0000
4.250 0.8460 0.01865 0.01059 -0.0828 0.6279 1.0000
4.500 0.8724 0.01846 0.01041 -0.0822 0.6162 1.0000
4.750 0.8970 0.01832 0.01027 -0.0814 0.6008 1.0000
5.000 0.9203 0.01827 0.01018 -0.0803 0.5817 1.0000
5.250 0.9395 0.01842 0.01034 -0.0788 0.5566 1.0000
5.500 0.9623 0.01844 0.01026 -0.0776 0.5304 1.0000
5.750 0.9833 0.01863 0.01032 -0.0763 0.5038 1.0000
6.000 1.0029 0.01896 0.01053 -0.0748 0.4794 1.0000
6.250 1.0211 0.01940 0.01088 -0.0732 0.4568 1.0000
6.500 1.0389 0.01989 0.01132 -0.0716 0.4362 1.0000
6.750 1.0564 0.02043 0.01179 -0.0700 0.4174 1.0000
7.000 1.0736 0.02099 0.01232 -0.0684 0.3997 1.0000
7.250 1.0898 0.02158 0.01290 -0.0668 0.3820 1.0000
7.500 1.1017 0.02222 0.01352 -0.0644 0.3605 1.0000
8.000 1.1188 0.02389 0.01496 -0.0590 0.3152 1.0000
8.250 1.1299 0.02475 0.01576 -0.0569 0.2981 1.0000
8.750 1.1548 0.02646 0.01747 -0.0533 0.2711 1.0000
9.000 1.1650 0.02748 0.01843 -0.0514 0.2583 1.0000
9.250 1.1753 0.02853 0.01949 -0.0496 0.2436 1.0000
9.500 1.1887 0.02944 0.02055 -0.0482 0.2309 1.0000
9.750 1.2007 0.03043 0.02164 -0.0467 0.2157 1.0000
10.000 1.2093 0.03166 0.02288 -0.0451 0.1974 1.0000
10.250 1.2146 0.03319 0.02432 -0.0433 0.1691 1.0000
10.500 1.2137 0.03530 0.02615 -0.0412 0.1297 1.0000
11.000 1.1969 0.04133 0.03143 -0.0364 0.0366 1.0000
11.250 1.1997 0.04350 0.03364 -0.0349 0.0314 1.0000
11.500 1.2022 0.04574 0.03597 -0.0336 0.0284 1.0000
12.000 1.2041 0.05067 0.04118 -0.0313 0.0250 1.0000
12.250 1.2034 0.05336 0.04404 -0.0303 0.0238 1.0000
12.500 1.2010 0.05631 0.04716 -0.0295 0.0229 1.0000
12.750 1.1968 0.05956 0.05059 -0.0288 0.0223 1.0000
13.000 1.1909 0.06314 0.05436 -0.0285 0.0218 1.0000
13.250 1.1837 0.06709 0.05849 -0.0284 0.0215 1.0000
13.500 1.1747 0.07145 0.06303 -0.0287 0.0211 1.0000
13.750 1.1649 0.07613 0.06787 -0.0293 0.0209 1.0000
14.000 1.1546 0.08108 0.07300 -0.0302 0.0207 1.0000
14.250 1.1444 0.08618 0.07826 -0.0314 0.0205 1.0000
14.500 1.1353 0.09123 0.08345 -0.0326 0.0203 1.0000
14.750 1.1277 0.09601 0.08836 -0.0338 0.0200 1.0000
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Polar data table (+)
Polar graphs
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