FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-140/20 (fx78k140-il) Reynolds number: 200,000 Max Cl/Cd: 54.18 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k140-il-200000.txt Download as CSV file: xf-fx78k140-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1736 0.12444 0.12044 -0.0790 0.8215 0.0302
-12.000 -0.1850 0.12316 0.11922 -0.0835 0.8203 0.0349
-11.750 -0.1821 0.11983 0.11590 -0.0848 0.8191 0.0350
-11.500 -0.1726 0.11609 0.11217 -0.0854 0.8180 0.0347
-11.250 -0.1734 0.11380 0.10993 -0.0882 0.8166 0.0351
-11.000 -0.1715 0.11067 0.10684 -0.0902 0.8154 0.0352
-10.750 -0.1667 0.10746 0.10366 -0.0916 0.8141 0.0352
-10.500 -0.1540 0.10195 0.09815 -0.0890 0.8133 0.0387
-10.250 -0.1505 0.09922 0.09543 -0.0903 0.8120 0.0386
-10.000 -0.1464 0.09645 0.09267 -0.0911 0.8106 0.0403
-9.750 -0.1461 0.09338 0.08962 -0.0921 0.8090 0.0426
-9.500 -0.1475 0.09023 0.08651 -0.0936 0.8078 0.0443
-9.250 -0.1476 0.08736 0.08364 -0.0949 0.8067 0.0446
-9.000 -0.1571 0.08390 0.08023 -0.0984 0.8055 0.0464
-8.750 -0.1658 0.07996 0.07639 -0.1039 0.8034 0.0470
-8.500 -0.1050 0.06002 0.05679 -0.0980 0.7972 0.0502
-8.250 -0.1084 0.05650 0.05329 -0.0995 0.7957 0.0508
-8.000 -0.2039 0.07245 0.06872 -0.1062 0.7966 0.0476
-7.750 -0.2119 0.07014 0.06626 -0.1050 0.7951 0.0477
-7.500 -0.2236 0.06414 0.06023 -0.1040 0.7936 0.0487
-7.250 -0.2130 0.06122 0.05741 -0.1029 0.7925 0.0504
-7.000 -0.2087 0.05914 0.05528 -0.1025 0.7901 0.0512
-6.750 -0.2043 0.05726 0.05335 -0.1018 0.7879 0.0539
-6.500 -0.2020 0.05521 0.05116 -0.1005 0.7855 0.0551
-6.250 -0.2045 0.05574 0.05105 -0.0963 0.7826 0.0610
-5.250 -0.2014 0.04249 0.03694 -0.0835 0.7727 0.0445
-5.000 -0.2060 0.03882 0.03243 -0.0769 0.7701 0.0362
-4.750 -0.1905 0.03752 0.03080 -0.0744 0.7681 0.0356
-4.500 -0.1680 0.03551 0.02841 -0.0729 0.7666 0.0351
-4.250 -0.1443 0.03250 0.02495 -0.0716 0.7655 0.0366
-4.000 -0.1713 0.03364 0.02617 -0.0645 0.7596 0.0382
-3.750 -0.1595 0.03327 0.02570 -0.0621 0.7564 0.0404
-3.500 -0.1343 0.03256 0.02482 -0.0614 0.7546 0.0438
-3.250 -0.1047 0.03188 0.02390 -0.0612 0.7532 0.0477
-3.000 -0.0730 0.03058 0.02261 -0.0616 0.7521 0.0558
-2.750 -0.0445 0.02993 0.02193 -0.0613 0.7509 0.0660
-2.500 -0.0962 0.03157 0.02349 -0.0495 0.7421 0.0626
-2.250 -0.0692 0.03106 0.02295 -0.0492 0.7401 0.0746
-2.000 -0.0402 0.03041 0.02240 -0.0491 0.7388 0.0965
-1.750 -0.0047 0.02969 0.02189 -0.0500 0.7378 0.1486
-1.500 0.1171 0.02734 0.02240 -0.0681 0.7384 0.9357
-1.250 0.2267 0.02809 0.02283 -0.0828 0.7386 0.9682
-1.000 0.3127 0.02829 0.02279 -0.0938 0.7384 0.9817
-0.750 0.4346 0.02807 0.02236 -0.1124 0.7389 1.0000
-0.500 0.4115 0.02969 0.02399 -0.1062 0.7304 1.0000
-0.250 0.4259 0.02987 0.02410 -0.1043 0.7274 1.0000
0.000 0.4514 0.02972 0.02386 -0.1037 0.7257 1.0000
0.250 0.4773 0.02962 0.02368 -0.1032 0.7245 1.0000
0.500 0.4323 0.03136 0.02544 -0.0932 0.7137 1.0000
0.750 0.4599 0.03128 0.02529 -0.0930 0.7121 1.0000
1.000 0.4901 0.03117 0.02511 -0.0932 0.7110 1.0000
1.250 0.4330 0.03249 0.02642 -0.0802 0.6996 1.0000
1.500 0.4692 0.03238 0.02626 -0.0815 0.6983 1.0000
1.750 0.5062 0.03231 0.02614 -0.0829 0.6973 1.0000
2.000 0.4588 0.03342 0.02721 -0.0712 0.6860 1.0000
2.250 0.4930 0.03332 0.02707 -0.0720 0.6846 1.0000
2.500 0.5292 0.03323 0.02695 -0.0733 0.6836 1.0000
2.750 0.5017 0.03433 0.02802 -0.0652 0.6726 1.0000
3.000 0.5346 0.03421 0.02787 -0.0658 0.6712 1.0000
3.250 0.5598 0.03430 0.02796 -0.0654 0.6685 1.0000
3.500 0.5522 0.03527 0.02890 -0.0607 0.6594 1.0000
3.750 0.5843 0.03512 0.02876 -0.0612 0.6579 1.0000
4.000 0.6193 0.03487 0.02853 -0.0620 0.6569 1.0000
4.250 0.6106 0.03601 0.02965 -0.0575 0.6462 1.0000
4.500 0.6427 0.03578 0.02945 -0.0579 0.6446 1.0000
4.750 0.6762 0.03553 0.02925 -0.0585 0.6436 1.0000
5.000 0.7124 0.03508 0.02885 -0.0593 0.6427 1.0000
5.250 0.7058 0.03624 0.03002 -0.0553 0.6313 1.0000
5.500 0.7250 0.03656 0.03038 -0.0543 0.6269 1.0000
5.750 0.7724 0.03551 0.02945 -0.0562 0.6290 1.0000
6.000 0.7689 0.03677 0.03072 -0.0529 0.6179 1.0000
6.250 0.8029 0.03627 0.03032 -0.0534 0.6167 1.0000
6.500 0.8398 0.03550 0.02965 -0.0541 0.6159 1.0000
6.750 0.8384 0.03675 0.03093 -0.0511 0.6045 1.0000
7.000 0.8470 0.03764 0.03193 -0.0492 0.5959 1.0000
7.250 0.8761 0.03724 0.03164 -0.0491 0.5927 1.0000
7.500 0.9118 0.03634 0.03087 -0.0495 0.5912 1.0000
7.750 0.9591 0.03407 0.02877 -0.0505 0.5903 1.0000
8.000 1.0281 0.02815 0.02309 -0.0517 0.5839 1.0000
8.250 1.1021 0.02034 0.01446 -0.0507 0.4407 1.0000
8.500 1.0785 0.02270 0.01623 -0.0446 0.3639 1.0000
8.750 1.0705 0.02459 0.01789 -0.0410 0.3195 1.0000
9.000 1.0442 0.02777 0.02050 -0.0359 0.2379 1.0000
9.250 1.0098 0.03178 0.02368 -0.0305 0.1261 1.0000
9.500 0.9860 0.03548 0.02671 -0.0263 0.0403 1.0000
9.750 0.9896 0.03729 0.02852 -0.0245 0.0318 1.0000
10.000 0.9937 0.03916 0.03048 -0.0227 0.0268 1.0000
10.250 0.9916 0.04160 0.03303 -0.0206 0.0237 1.0000
10.500 0.9930 0.04380 0.03535 -0.0188 0.0224 1.0000
10.750 1.0004 0.04548 0.03710 -0.0176 0.0193 1.0000
11.000 1.0048 0.04746 0.03915 -0.0161 0.0182 1.0000
11.250 1.0092 0.04942 0.04115 -0.0146 0.0172 1.0000
11.500 1.0190 0.05087 0.04273 -0.0132 0.0176 1.0000
11.750 1.0286 0.05231 0.04416 -0.0115 0.0164 1.0000
12.000 1.0569 0.05256 0.04440 -0.0089 0.0156 1.0000
12.250 1.0807 0.05336 0.04529 -0.0079 0.0158 1.0000
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