FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 78-K-140 A/20 (fx78k140a20-il) Reynolds number: 500,000 Max Cl/Cd: 111.35 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx78k140a20-il-500000-n5.txt Download as CSV file: xf-fx78k140a20-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 78-K-140 A/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1782 0.08418 0.08058 -0.0971 0.7189 0.0053
-10.250 -0.1870 0.07784 0.07428 -0.1005 0.7180 0.0051
-10.000 -0.2070 0.06939 0.06590 -0.1056 0.7171 0.0050
-9.250 -0.3914 0.03103 0.02669 -0.1094 0.7132 0.0046
-9.000 -0.4052 0.02642 0.02152 -0.1049 0.7120 0.0048
-8.750 -0.3969 0.02434 0.01911 -0.1026 0.7112 0.0045
-8.500 -0.3870 0.02224 0.01662 -0.1004 0.7103 0.0050
-8.250 -0.3704 0.02103 0.01522 -0.0990 0.7093 0.0052
-8.000 -0.3492 0.02050 0.01462 -0.0983 0.7083 0.0056
-7.750 -0.3307 0.01929 0.01319 -0.0971 0.7073 0.0057
-7.500 -0.3084 0.01872 0.01252 -0.0964 0.7061 0.0063
-7.250 -0.2848 0.01838 0.01209 -0.0960 0.7049 0.0068
-7.000 -0.2615 0.01780 0.01135 -0.0954 0.7036 0.0076
-6.750 -0.2414 0.01655 0.00989 -0.0943 0.7026 0.0078
-6.500 -0.2189 0.01590 0.00915 -0.0937 0.7016 0.0086
-6.250 -0.1950 0.01541 0.00856 -0.0932 0.7007 0.0092
-6.000 -0.1707 0.01499 0.00806 -0.0928 0.6999 0.0098
-5.750 -0.1471 0.01442 0.00740 -0.0921 0.6990 0.0105
-5.500 -0.1221 0.01412 0.00702 -0.0918 0.6981 0.0115
-5.250 -0.0977 0.01372 0.00652 -0.0914 0.6972 0.0119
-5.000 -0.0751 0.01309 0.00581 -0.0905 0.6962 0.0134
-4.750 -0.0512 0.01273 0.00543 -0.0900 0.6951 0.0147
-4.500 -0.0266 0.01246 0.00511 -0.0895 0.6940 0.0169
-4.250 -0.0016 0.01223 0.00484 -0.0891 0.6928 0.0194
-4.000 0.0229 0.01195 0.00455 -0.0887 0.6915 0.0235
-3.750 0.0484 0.01178 0.00436 -0.0884 0.6903 0.0281
-3.500 0.0735 0.01155 0.00418 -0.0881 0.6891 0.0374
-3.250 0.0989 0.01137 0.00400 -0.0879 0.6881 0.0474
-3.000 0.1248 0.01122 0.00383 -0.0877 0.6871 0.0567
-2.750 0.1505 0.01106 0.00368 -0.0875 0.6861 0.0684
-2.500 0.1761 0.01087 0.00353 -0.0872 0.6850 0.0867
-2.250 0.2017 0.01069 0.00340 -0.0870 0.6841 0.1110
-2.000 0.2255 0.01037 0.00328 -0.0866 0.6832 0.1756
-1.750 0.2473 0.01001 0.00323 -0.0858 0.6820 0.2673
-1.500 0.2686 0.00967 0.00319 -0.0849 0.6805 0.3581
-1.250 0.2877 0.00924 0.00313 -0.0835 0.6789 0.4735
-1.000 0.3001 0.00859 0.00305 -0.0806 0.6774 0.6442
-0.750 0.3158 0.00836 0.00337 -0.0777 0.6759 0.7869
-0.500 0.3400 0.00853 0.00353 -0.0768 0.6745 0.8350
-0.250 0.3635 0.00868 0.00364 -0.0758 0.6734 0.8569
0.000 0.3878 0.00883 0.00378 -0.0749 0.6722 0.8718
0.250 0.4128 0.00897 0.00391 -0.0741 0.6711 0.8846
0.500 0.4390 0.00905 0.00399 -0.0736 0.6700 0.8931
0.750 0.4632 0.00913 0.00404 -0.0729 0.6688 0.8996
1.000 0.4892 0.00916 0.00409 -0.0727 0.6670 0.9020
1.250 0.5153 0.00918 0.00412 -0.0725 0.6651 0.9036
1.500 0.5418 0.00919 0.00412 -0.0725 0.6632 0.9048
1.750 0.5684 0.00918 0.00411 -0.0725 0.6613 0.9064
2.000 0.5954 0.00915 0.00407 -0.0725 0.6594 0.9081
2.250 0.6228 0.00913 0.00402 -0.0727 0.6577 0.9091
2.500 0.6505 0.00911 0.00398 -0.0729 0.6561 0.9100
2.750 0.6754 0.00915 0.00406 -0.0726 0.6537 0.9109
3.000 0.7008 0.00918 0.00413 -0.0724 0.6510 0.9116
3.250 0.7269 0.00918 0.00415 -0.0724 0.6484 0.9123
3.500 0.7534 0.00917 0.00415 -0.0724 0.6459 0.9130
3.750 0.7803 0.00916 0.00414 -0.0725 0.6439 0.9138
4.000 0.8073 0.00916 0.00418 -0.0726 0.6416 0.9143
4.250 0.8318 0.00921 0.00430 -0.0722 0.6382 0.9149
4.500 0.8573 0.00923 0.00438 -0.0721 0.6348 0.9155
4.750 0.8836 0.00924 0.00443 -0.0721 0.6320 0.9161
5.000 0.9108 0.00923 0.00445 -0.0722 0.6293 0.9166
5.250 0.9348 0.00930 0.00461 -0.0718 0.6249 0.9174
5.500 0.9595 0.00935 0.00474 -0.0714 0.6208 0.9181
5.750 0.9853 0.00936 0.00480 -0.0713 0.6172 0.9187
6.000 1.0092 0.00941 0.00493 -0.0709 0.6111 0.9195
6.250 1.0318 0.00939 0.00496 -0.0700 0.5993 0.9206
6.500 1.0489 0.00942 0.00493 -0.0680 0.5713 0.9221
6.750 1.0537 0.00982 0.00509 -0.0637 0.5225 0.9240
7.000 1.0404 0.01075 0.00571 -0.0563 0.4643 0.9269
7.250 1.0184 0.01297 0.00753 -0.0497 0.3860 0.9307
7.500 1.0142 0.01590 0.01015 -0.0490 0.3206 0.9339
8.000 0.9885 0.02217 0.01541 -0.0443 0.1366 0.9403
8.250 0.9901 0.02429 0.01721 -0.0431 0.0777 0.9427
8.500 0.9899 0.02659 0.01918 -0.0418 0.0195 0.9454
8.750 1.0050 0.02778 0.02037 -0.0417 0.0113 0.9472
9.000 1.0218 0.02886 0.02151 -0.0416 0.0092 0.9492
9.250 1.0377 0.03003 0.02275 -0.0415 0.0072 0.9512
9.500 1.0529 0.03126 0.02406 -0.0415 0.0061 0.9535
10.000 1.0796 0.03420 0.02717 -0.0412 0.0048 0.9595
10.250 1.1002 0.03516 0.02817 -0.0419 0.0040 0.9632
10.500 1.1109 0.03696 0.03008 -0.0416 0.0045 0.9681
10.750 1.1287 0.03804 0.03121 -0.0421 0.0035 0.9824
11.250 1.1491 0.04154 0.03487 -0.0406 0.0033 1.0000
11.500 1.1583 0.04317 0.03655 -0.0400 0.0030 1.0000
11.750 1.1644 0.04514 0.03861 -0.0390 0.0030 1.0000
12.000 1.1709 0.04708 0.04063 -0.0381 0.0030 1.0000
12.250 1.1765 0.04910 0.04273 -0.0373 0.0029 1.0000
12.500 1.1775 0.05157 0.04528 -0.0360 0.0026 1.0000
12.750 1.1805 0.05386 0.04766 -0.0350 0.0026 1.0000
13.000 1.1894 0.05569 0.04962 -0.0342 0.0023 1.0000
13.250 1.1964 0.05763 0.05164 -0.0336 0.0024 1.0000
13.500 1.2015 0.05977 0.05390 -0.0326 0.0023 1.0000
13.750 1.2074 0.06187 0.05612 -0.0317 0.0022 1.0000
14.000 1.2137 0.06397 0.05833 -0.0310 0.0021 1.0000
14.250 1.2192 0.06619 0.06070 -0.0302 0.0022 1.0000
14.500 1.2229 0.06861 0.06328 -0.0292 0.0021 1.0000
14.750 1.2273 0.07102 0.06582 -0.0287 0.0022 1.0000
15.000 1.2269 0.07412 0.06915 -0.0275 0.0020 1.0000
15.250 1.2289 0.07700 0.07217 -0.0272 0.0021 1.0000
15.500 1.2258 0.08060 0.07598 -0.0267 0.0021 1.0000
15.750 1.2192 0.08483 0.08044 -0.0263 0.0020 1.0000
16.000 1.2139 0.08895 0.08475 -0.0265 0.0020 1.0000
16.250 1.2058 0.09364 0.08964 -0.0270 0.0021 1.0000
16.500 1.1951 0.09887 0.09508 -0.0279 0.0020 1.0000
16.750 1.1790 0.10514 0.10159 -0.0291 0.0020 1.0000
17.000 1.1709 0.11026 0.10685 -0.0308 0.0021 1.0000
17.250 1.1567 0.11672 0.11351 -0.0331 0.0021 1.0000
17.500 1.1371 0.12452 0.12153 -0.0361 0.0021 1.0000
17.750 1.1190 0.13244 0.12964 -0.0397 0.0021 1.0000
18.000 1.1009 0.14079 0.13817 -0.0440 0.0021 1.0000
18.250 1.0930 0.14711 0.14460 -0.0477 0.0022 1.0000
18.500 1.0646 0.15930 0.15702 -0.0545 0.0021 1.0000
18.750 1.0568 0.16656 0.16436 -0.0591 0.0022 1.0000
19.000 1.0281 0.18162 0.17961 -0.0679 0.0022 1.0000
19.250 1.0121 0.19400 0.19208 -0.0748 0.0023 1.0000
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