FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-140/20 (fx78k140-il) Reynolds number: 100,000 Max Cl/Cd: 27.24 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k140-il-100000-n5.txt Download as CSV file: xf-fx78k140-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-140/20
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1048 0.10533 0.10038 -0.0730 0.7922 0.0427
-11.250 -0.1038 0.10087 0.09590 -0.0747 0.7912 0.0300
-11.000 -0.1022 0.09757 0.09263 -0.0765 0.7900 0.0314
-10.750 -0.0999 0.09407 0.08913 -0.0780 0.7889 0.0299
-10.500 -0.1013 0.09036 0.08545 -0.0799 0.7878 0.0323
-10.250 -0.0985 0.08688 0.08198 -0.0811 0.7867 0.0306
-10.000 -0.0990 0.08312 0.07823 -0.0827 0.7856 0.0307
-9.750 -0.1010 0.07908 0.07422 -0.0842 0.7844 0.0305
-9.250 -0.1832 0.08240 0.07723 -0.0947 0.7886 0.0240
-9.000 -0.1890 0.07748 0.07236 -0.0990 0.7866 0.0244
-8.750 -0.1924 0.07418 0.06909 -0.1003 0.7848 0.0236
-8.500 -0.2058 0.06929 0.06418 -0.1031 0.7826 0.0241
-8.250 -0.2140 0.06699 0.06187 -0.1018 0.7807 0.0231
-8.000 -0.2268 0.06362 0.05838 -0.1008 0.7789 0.0236
-7.750 -0.2324 0.06070 0.05535 -0.1002 0.7764 0.0235
-7.500 -0.2393 0.05730 0.05178 -0.0990 0.7739 0.0236
-7.250 -0.2454 0.05377 0.04799 -0.0970 0.7714 0.0238
-7.000 -0.2455 0.05100 0.04497 -0.0949 0.7691 0.0236
-6.750 -0.2462 0.04776 0.04135 -0.0920 0.7671 0.0237
-6.500 -0.2421 0.04499 0.03820 -0.0893 0.7656 0.0238
-6.250 -0.2371 0.04252 0.03532 -0.0867 0.7633 0.0240
-6.000 -0.2310 0.04047 0.03282 -0.0840 0.7601 0.0244
-5.750 -0.2219 0.03837 0.03034 -0.0816 0.7573 0.0248
-5.500 -0.2091 0.03687 0.02867 -0.0798 0.7551 0.0268
-5.250 -0.1919 0.03594 0.02750 -0.0783 0.7535 0.0293
-5.000 -0.1726 0.03453 0.02571 -0.0768 0.7522 0.0317
-4.750 -0.1501 0.03295 0.02373 -0.0755 0.7511 0.0336
-4.500 -0.1397 0.03255 0.02308 -0.0735 0.7462 0.0347
-4.250 -0.1225 0.03164 0.02211 -0.0721 0.7435 0.0385
-4.000 -0.1025 0.03117 0.02152 -0.0710 0.7415 0.0435
-3.750 -0.0800 0.03048 0.02061 -0.0700 0.7399 0.0476
-3.500 -0.0591 0.02972 0.01988 -0.0689 0.7385 0.0548
-3.250 -0.0477 0.02969 0.01978 -0.0666 0.7349 0.0630
-3.000 -0.0403 0.02976 0.01983 -0.0638 0.7307 0.0698
-2.750 -0.0238 0.02948 0.01948 -0.0620 0.7282 0.0813
-2.500 -0.0028 0.02915 0.01913 -0.0608 0.7263 0.1036
-2.250 0.0184 0.02868 0.01883 -0.0598 0.7248 0.1414
-1.750 0.1145 0.02626 0.01898 -0.0674 0.7240 0.8475
-1.500 0.1986 0.02685 0.01930 -0.0774 0.7241 0.9290
-1.250 0.3143 0.02746 0.01952 -0.0939 0.7247 0.9784
-1.000 0.3957 0.02743 0.01924 -0.1050 0.7246 0.9973
-0.750 0.4086 0.02831 0.02006 -0.1044 0.7195 1.0000
-0.500 0.4158 0.02887 0.02054 -0.1018 0.7155 1.0000
-0.250 0.4309 0.02907 0.02064 -0.1001 0.7130 1.0000
0.000 0.4493 0.02916 0.02063 -0.0986 0.7113 1.0000
0.500 0.4470 0.03075 0.02213 -0.0910 0.7005 1.0000
0.750 0.4652 0.03085 0.02216 -0.0895 0.6984 1.0000
1.000 0.4871 0.03087 0.02209 -0.0884 0.6969 1.0000
1.250 0.4615 0.03223 0.02344 -0.0810 0.6873 1.0000
1.500 0.4814 0.03234 0.02348 -0.0798 0.6851 1.0000
1.750 0.5056 0.03235 0.02343 -0.0791 0.6836 1.0000
2.250 0.4999 0.03366 0.02465 -0.0701 0.6716 1.0000
2.500 0.5264 0.03371 0.02466 -0.0699 0.6700 1.0000
2.750 0.5076 0.03482 0.02574 -0.0634 0.6604 1.0000
3.000 0.5313 0.03495 0.02584 -0.0628 0.6581 1.0000
3.250 0.5597 0.03492 0.02579 -0.0628 0.6565 1.0000
3.500 0.5490 0.03608 0.02693 -0.0579 0.6469 1.0000
3.750 0.5737 0.03619 0.02706 -0.0575 0.6446 1.0000
4.000 0.6024 0.03614 0.02702 -0.0575 0.6430 1.0000
4.250 0.5968 0.03729 0.02816 -0.0535 0.6330 1.0000
4.500 0.6229 0.03734 0.02824 -0.0533 0.6308 1.0000
4.750 0.6510 0.03729 0.02825 -0.0532 0.6290 1.0000
5.000 0.6481 0.03852 0.02951 -0.0498 0.6190 1.0000
5.250 0.6759 0.03845 0.02949 -0.0498 0.6168 1.0000
5.750 0.7037 0.03958 0.03072 -0.0468 0.6045 1.0000
6.000 0.7270 0.03967 0.03088 -0.0463 0.6008 1.0000
6.250 0.7343 0.04065 0.03197 -0.0443 0.5922 1.0000
6.500 0.7625 0.04044 0.03186 -0.0443 0.5898 1.0000
7.000 0.7938 0.04153 0.03315 -0.0419 0.5771 1.0000
7.250 0.8209 0.04140 0.03314 -0.0417 0.5744 1.0000
7.500 0.8276 0.04246 0.03434 -0.0399 0.5642 1.0000
7.750 0.8574 0.04202 0.03407 -0.0398 0.5619 1.0000
8.000 0.8627 0.04333 0.03549 -0.0380 0.5512 1.0000
8.250 0.8920 0.04289 0.03526 -0.0377 0.5485 1.0000
8.500 0.9003 0.04391 0.03641 -0.0361 0.5378 1.0000
9.500 1.0080 0.03701 0.02969 -0.0292 0.4063 1.0000
9.750 1.0085 0.03776 0.02950 -0.0256 0.2886 1.0000
10.000 0.9867 0.04122 0.03208 -0.0218 0.1807 1.0000
10.250 0.9686 0.04475 0.03473 -0.0187 0.0733 1.0000
10.500 0.9649 0.04727 0.03688 -0.0165 0.0357 1.0000
10.750 0.9689 0.04926 0.03892 -0.0150 0.0281 1.0000
11.000 0.9724 0.05136 0.04109 -0.0134 0.0241 1.0000
11.250 0.9765 0.05345 0.04331 -0.0121 0.0212 1.0000
11.500 0.9833 0.05528 0.04533 -0.0112 0.0189 1.0000
11.750 0.9873 0.05745 0.04767 -0.0100 0.0187 1.0000
12.000 0.9891 0.05984 0.05013 -0.0088 0.0163 1.0000
12.250 0.9934 0.06196 0.05237 -0.0078 0.0159 1.0000
12.500 0.9985 0.06401 0.05450 -0.0065 0.0155 1.0000
12.750 1.0079 0.06559 0.05616 -0.0047 0.0147 1.0000
13.000 1.0230 0.06677 0.05745 -0.0033 0.0143 1.0000
13.250 1.0389 0.06800 0.05883 -0.0021 0.0139 1.0000
13.500 1.0543 0.06943 0.06043 -0.0011 0.0135 1.0000
13.750 1.0667 0.07141 0.06261 0.0000 0.0120 1.0000
14.000 1.0774 0.07354 0.06495 0.0009 0.0116 1.0000
14.250 1.0799 0.07608 0.06764 0.0012 0.0108 1.0000
14.500 1.0929 0.07872 0.07067 0.0025 0.0116 1.0000
14.750 1.0898 0.08185 0.07394 0.0026 0.0105 1.0000
15.000 1.0870 0.08572 0.07805 0.0031 0.0102 1.0000
15.250 1.0836 0.08941 0.08195 0.0031 0.0101 1.0000
15.500 1.0751 0.09415 0.08696 0.0031 0.0099 1.0000
15.750 1.0697 0.09837 0.09150 0.0027 0.0105 1.0000
16.000 1.0551 0.10404 0.09743 0.0018 0.0103 1.0000
16.250 1.0435 0.10933 0.10295 0.0004 0.0103 1.0000
16.500 1.0295 0.11532 0.10920 -0.0016 0.0105 1.0000
16.750 1.0146 0.12177 0.11585 -0.0042 0.0105 1.0000
17.000 0.9979 0.12890 0.12320 -0.0075 0.0105 1.0000
17.250 0.9803 0.13663 0.13108 -0.0114 0.0103 1.0000
17.500 0.9540 0.14784 0.14260 -0.0177 0.0111 1.0000
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