WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WB-140/35/FB 14% (wb140-il) Reynolds number: 50,000 Max Cl/Cd: 31.88 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb140-il-50000-n5.txt Download as CSV file: xf-wb140-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3728 0.10618 0.09949 -0.0530 1.0000 0.0599
-10.500 -0.3808 0.10247 0.09589 -0.0534 1.0000 0.0597
-10.250 -0.3918 0.09896 0.09250 -0.0532 1.0000 0.0593
-10.000 -0.4066 0.09568 0.08936 -0.0526 1.0000 0.0589
-9.750 -0.4261 0.09275 0.08657 -0.0512 1.0000 0.0585
-9.500 -0.4503 0.09015 0.08411 -0.0491 1.0000 0.0581
-9.250 -0.4783 0.08768 0.08179 -0.0469 1.0000 0.0576
-9.000 -0.4953 0.07997 0.07409 -0.0538 0.9913 0.0567
-8.750 -0.5105 0.07024 0.06418 -0.0621 0.9802 0.0558
-8.500 -0.5228 0.06189 0.05544 -0.0672 0.9705 0.0553
-8.250 -0.5264 0.05556 0.04861 -0.0694 0.9620 0.0553
-8.000 -0.5172 0.05037 0.04284 -0.0714 0.9558 0.0561
-7.750 -0.5045 0.04678 0.03874 -0.0720 0.9499 0.0582
-7.500 -0.4900 0.04359 0.03497 -0.0721 0.9443 0.0606
-7.250 -0.4680 0.04076 0.03151 -0.0728 0.9402 0.0624
-7.000 -0.4416 0.03880 0.02937 -0.0738 0.9372 0.0642
-6.750 -0.4237 0.03748 0.02787 -0.0729 0.9321 0.0661
-6.500 -0.4017 0.03632 0.02651 -0.0727 0.9274 0.0699
-6.250 -0.3750 0.03506 0.02488 -0.0732 0.9238 0.0748
-6.000 -0.3464 0.03403 0.02374 -0.0741 0.9208 0.0789
-5.750 -0.3197 0.03319 0.02274 -0.0744 0.9178 0.0838
-5.250 -0.2766 0.03212 0.02159 -0.0731 0.9092 0.0992
-5.000 -0.2480 0.03222 0.02177 -0.0738 0.9055 0.1193
-4.750 -0.2154 0.03213 0.02137 -0.0748 0.9025 0.1558
-4.500 -0.1993 0.03483 0.02242 -0.0728 0.8961 0.1784
-4.250 -0.1737 0.03274 0.02039 -0.0734 0.8933 0.1969
-4.000 -0.1452 0.03105 0.01911 -0.0741 0.8908 0.2139
-3.750 -0.1156 0.03050 0.01869 -0.0751 0.8878 0.2232
-3.500 -0.0842 0.03028 0.01860 -0.0765 0.8850 0.2360
-3.250 -0.0657 0.03044 0.01863 -0.0755 0.8800 0.2536
-3.000 -0.0433 0.03046 0.01860 -0.0751 0.8753 0.2657
-2.750 -0.0146 0.03040 0.01849 -0.0758 0.8714 0.2798
-2.500 0.0184 0.03029 0.01837 -0.0773 0.8682 0.2968
-2.250 0.0380 0.03039 0.01846 -0.0764 0.8626 0.3090
-2.000 0.0617 0.03045 0.01847 -0.0762 0.8571 0.3193
-1.750 0.0924 0.03042 0.01844 -0.0771 0.8531 0.3333
-1.500 0.1277 0.03033 0.01839 -0.0789 0.8499 0.3557
-1.250 0.1406 0.03055 0.01870 -0.0768 0.8420 0.3812
-1.000 0.1709 0.03039 0.01871 -0.0776 0.8364 0.4345
-0.750 0.2078 0.02996 0.01863 -0.0791 0.8325 0.5282
-0.500 0.2183 0.03003 0.01902 -0.0761 0.8227 0.6062
-0.250 0.2501 0.02970 0.01913 -0.0758 0.8177 0.7571
0.000 0.2904 0.02981 0.01932 -0.0780 0.8122 0.8998
0.250 0.3176 0.03019 0.01961 -0.0786 0.8042 1.0000
0.500 0.3527 0.03031 0.01958 -0.0801 0.7996 1.0000
0.750 0.3654 0.03088 0.02006 -0.0780 0.7903 1.0000
1.000 0.3963 0.03104 0.02012 -0.0787 0.7843 1.0000
1.250 0.4160 0.03145 0.02045 -0.0777 0.7757 1.0000
1.500 0.4452 0.03160 0.02052 -0.0780 0.7686 1.0000
1.750 0.4668 0.03195 0.02082 -0.0772 0.7599 1.0000
2.000 0.4977 0.03201 0.02084 -0.0776 0.7530 1.0000
2.250 0.5207 0.03231 0.02112 -0.0770 0.7442 1.0000
2.750 0.5804 0.03226 0.02104 -0.0771 0.7276 1.0000
3.000 0.6204 0.03176 0.02052 -0.0783 0.7215 1.0000
3.250 0.6424 0.03197 0.02075 -0.0772 0.7103 1.0000
3.750 0.6991 0.03200 0.02085 -0.0768 0.6930 1.0000
4.000 0.7134 0.03254 0.02144 -0.0748 0.6797 1.0000
4.250 0.7258 0.03308 0.02205 -0.0725 0.6651 1.0000
4.500 0.7370 0.03356 0.02260 -0.0701 0.6500 1.0000
4.750 0.7516 0.03385 0.02294 -0.0680 0.6354 1.0000
5.000 0.7695 0.03398 0.02314 -0.0663 0.6212 1.0000
5.250 0.7907 0.03396 0.02322 -0.0650 0.6080 1.0000
5.500 0.8268 0.03304 0.02239 -0.0650 0.5999 1.0000
5.750 0.8425 0.03332 0.02275 -0.0631 0.5842 1.0000
6.000 0.8607 0.03351 0.02302 -0.0615 0.5685 1.0000
6.250 0.8814 0.03357 0.02320 -0.0602 0.5528 1.0000
6.500 0.9055 0.03340 0.02311 -0.0591 0.5370 1.0000
6.750 0.9325 0.03303 0.02280 -0.0582 0.5207 1.0000
7.000 0.9609 0.03264 0.02243 -0.0574 0.5031 1.0000
7.250 0.9879 0.03245 0.02227 -0.0565 0.4843 1.0000
7.500 1.0128 0.03249 0.02228 -0.0555 0.4651 1.0000
7.750 1.0363 0.03273 0.02250 -0.0545 0.4466 1.0000
8.000 1.0580 0.03319 0.02295 -0.0535 0.4295 1.0000
8.250 1.0782 0.03383 0.02365 -0.0524 0.4138 1.0000
8.500 1.0980 0.03457 0.02442 -0.0514 0.3994 1.0000
8.750 1.1193 0.03526 0.02516 -0.0506 0.3863 1.0000
9.000 1.1353 0.03625 0.02628 -0.0493 0.3737 1.0000
9.250 1.1473 0.03734 0.02749 -0.0476 0.3604 1.0000
9.500 1.1565 0.03840 0.02861 -0.0456 0.3457 1.0000
9.750 1.1639 0.03949 0.02977 -0.0435 0.3304 1.0000
10.000 1.1735 0.04053 0.03081 -0.0417 0.3165 1.0000
10.250 1.1822 0.04182 0.03222 -0.0400 0.3042 1.0000
10.500 1.1878 0.04331 0.03385 -0.0383 0.2915 1.0000
10.750 1.1923 0.04481 0.03543 -0.0365 0.2783 1.0000
11.000 1.2004 0.04611 0.03677 -0.0349 0.2671 1.0000
11.250 1.2054 0.04773 0.03850 -0.0334 0.2553 1.0000
11.500 1.2023 0.04998 0.04089 -0.0317 0.2402 1.0000
11.750 1.1943 0.05278 0.04385 -0.0303 0.2220 1.0000
12.000 1.1853 0.05588 0.04713 -0.0293 0.2004 1.0000
12.250 1.1781 0.05908 0.05044 -0.0285 0.1772 1.0000
12.500 1.1708 0.06251 0.05390 -0.0279 0.1493 1.0000
13.000 1.1410 0.07180 0.06266 -0.0277 0.0774 1.0000
13.250 1.1258 0.07706 0.06782 -0.0282 0.0672 1.0000
13.500 1.1128 0.08233 0.07312 -0.0289 0.0602 1.0000
13.750 1.0991 0.08793 0.07878 -0.0301 0.0561 1.0000
14.000 1.0886 0.09324 0.08421 -0.0313 0.0526 1.0000
14.250 1.0793 0.09851 0.08963 -0.0327 0.0497 1.0000
14.500 1.0704 0.10381 0.09506 -0.0343 0.0475 1.0000
14.750 1.0620 0.10905 0.10039 -0.0360 0.0457 1.0000
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Polar data table (+)
Polar graphs
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