FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 78-K-140 A/20 (fx78k140a20-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.4 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx78k140a20-il-1000000.txt Download as CSV file: xf-fx78k140a20-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3442 0.02721 0.02331 -0.1127 0.7166 0.0067
-8.500 -0.3444 0.02426 0.01998 -0.1091 0.7153 0.0066
-8.250 -0.3271 0.02340 0.01898 -0.1078 0.7145 0.0064
-8.000 -0.3285 0.01986 0.01497 -0.1036 0.7137 0.0067
-7.750 -0.3117 0.01858 0.01349 -0.1021 0.7128 0.0066
-7.500 -0.2923 0.01780 0.01263 -0.1010 0.7118 0.0072
-7.250 -0.2715 0.01703 0.01175 -0.1001 0.7108 0.0074
-7.000 -0.2514 0.01588 0.01040 -0.0989 0.7098 0.0075
-6.750 -0.2301 0.01491 0.00927 -0.0979 0.7087 0.0077
-6.500 -0.2076 0.01413 0.00837 -0.0970 0.7076 0.0082
-6.250 -0.1850 0.01341 0.00754 -0.0962 0.7066 0.0084
-6.000 -0.1614 0.01288 0.00691 -0.0956 0.7058 0.0091
-5.750 -0.1368 0.01249 0.00646 -0.0951 0.7049 0.0095
-5.500 -0.1162 0.01166 0.00548 -0.0939 0.7039 0.0106
-5.250 -0.0918 0.01132 0.00511 -0.0934 0.7029 0.0118
-5.000 -0.0661 0.01118 0.00494 -0.0931 0.7016 0.0135
-4.750 -0.0413 0.01095 0.00468 -0.0927 0.7007 0.0145
-4.500 -0.0180 0.01055 0.00427 -0.0920 0.6999 0.0183
-4.250 0.0077 0.01041 0.00412 -0.0918 0.6990 0.0203
-4.000 0.0317 0.01008 0.00378 -0.0911 0.6979 0.0254
-3.750 0.0577 0.00997 0.00367 -0.0910 0.6968 0.0295
-3.500 0.0823 0.00970 0.00343 -0.0905 0.6956 0.0393
-3.250 0.1078 0.00952 0.00327 -0.0902 0.6946 0.0490
-3.000 0.1335 0.00936 0.00314 -0.0899 0.6935 0.0619
-2.750 0.1593 0.00920 0.00301 -0.0897 0.6924 0.0770
-2.500 0.1845 0.00899 0.00288 -0.0894 0.6914 0.1056
-2.250 0.2085 0.00872 0.00278 -0.0889 0.6904 0.1599
-2.000 0.2304 0.00834 0.00269 -0.0881 0.6893 0.2554
-1.750 0.2506 0.00796 0.00265 -0.0869 0.6881 0.3717
-1.500 0.2634 0.00731 0.00258 -0.0842 0.6869 0.5520
-1.250 0.2647 0.00657 0.00268 -0.0785 0.6857 0.7898
-1.000 0.2885 0.00670 0.00285 -0.0775 0.6844 0.8351
-0.750 0.3145 0.00678 0.00290 -0.0772 0.6831 0.8460
-0.500 0.3403 0.00686 0.00294 -0.0768 0.6818 0.8545
-0.250 0.3679 0.00692 0.00300 -0.0768 0.6806 0.8602
0.000 0.3938 0.00701 0.00306 -0.0764 0.6793 0.8692
0.250 0.4204 0.00714 0.00320 -0.0760 0.6781 0.8797
0.500 0.4476 0.00726 0.00333 -0.0757 0.6770 0.8897
0.750 0.4738 0.00734 0.00341 -0.0753 0.6757 0.8978
1.000 0.5006 0.00750 0.00356 -0.0750 0.6739 0.9057
1.250 0.5248 0.00749 0.00357 -0.0743 0.6723 0.9107
1.500 0.5508 0.00745 0.00355 -0.0739 0.6705 0.9138
1.750 0.5774 0.00743 0.00354 -0.0739 0.6687 0.9153
2.000 0.6045 0.00740 0.00350 -0.0740 0.6669 0.9163
2.250 0.6320 0.00736 0.00345 -0.0742 0.6651 0.9173
2.500 0.6596 0.00732 0.00340 -0.0743 0.6633 0.9185
2.750 0.6870 0.00732 0.00339 -0.0745 0.6616 0.9198
3.000 0.7139 0.00736 0.00342 -0.0746 0.6597 0.9209
3.250 0.7392 0.00733 0.00343 -0.0744 0.6575 0.9216
3.500 0.7654 0.00731 0.00344 -0.0743 0.6553 0.9221
3.750 0.7921 0.00729 0.00345 -0.0744 0.6531 0.9225
4.000 0.8191 0.00727 0.00343 -0.0745 0.6509 0.9230
4.250 0.8463 0.00724 0.00340 -0.0746 0.6483 0.9235
4.500 0.8731 0.00725 0.00342 -0.0747 0.6459 0.9240
4.750 0.8982 0.00722 0.00348 -0.0744 0.6433 0.9246
5.000 0.9242 0.00721 0.00350 -0.0743 0.6403 0.9251
5.250 0.9507 0.00718 0.00351 -0.0743 0.6372 0.9256
5.500 0.9761 0.00712 0.00346 -0.0741 0.6313 0.9261
5.750 0.9986 0.00700 0.00335 -0.0731 0.6194 0.9268
6.000 1.0205 0.00698 0.00335 -0.0721 0.6052 0.9275
6.250 1.0392 0.00705 0.00339 -0.0704 0.5802 0.9286
6.500 1.0468 0.00746 0.00360 -0.0666 0.5345 0.9302
6.750 1.0388 0.00837 0.00419 -0.0599 0.4666 0.9325
7.000 1.0302 0.00944 0.00498 -0.0536 0.4072 0.9349
7.250 1.0223 0.01161 0.00670 -0.0497 0.3164 0.9370
7.500 1.0230 0.01574 0.01024 -0.0522 0.1966 0.9391
7.750 1.0342 0.01780 0.01203 -0.0530 0.1394 0.9402
8.000 1.0282 0.02071 0.01445 -0.0515 0.0519 0.9420
8.250 1.0321 0.02260 0.01614 -0.0502 0.0132 0.9437
8.500 1.0462 0.02372 0.01730 -0.0496 0.0092 0.9451
8.750 1.0618 0.02470 0.01833 -0.0491 0.0084 0.9464
9.000 1.0707 0.02616 0.01986 -0.0479 0.0063 0.9478
9.250 1.0826 0.02738 0.02116 -0.0471 0.0064 0.9492
9.500 1.0962 0.02848 0.02233 -0.0464 0.0061 0.9505
9.750 1.1111 0.02953 0.02343 -0.0460 0.0057 0.9521
10.000 1.1267 0.03053 0.02447 -0.0457 0.0057 0.9541
10.250 1.1328 0.03228 0.02633 -0.0444 0.0053 0.9567
10.500 1.1464 0.03353 0.02762 -0.0441 0.0050 0.9594
10.750 1.1563 0.03513 0.02930 -0.0434 0.0049 0.9628
11.000 1.1687 0.03661 0.03084 -0.0432 0.0046 0.9678
11.250 1.1792 0.03842 0.03273 -0.0429 0.0047 0.9748
11.500 1.1822 0.04112 0.03554 -0.0417 0.0039 1.0000
11.750 1.1855 0.04320 0.03769 -0.0403 0.0040 1.0000
12.000 1.1936 0.04490 0.03946 -0.0393 0.0039 1.0000
12.250 1.1988 0.04673 0.04136 -0.0376 0.0040 1.0000
12.500 1.2130 0.04805 0.04276 -0.0374 0.0037 1.0000
12.750 1.2197 0.04966 0.04444 -0.0355 0.0039 1.0000
13.000 1.2307 0.05130 0.04618 -0.0349 0.0033 1.0000
13.250 1.2409 0.05282 0.04780 -0.0338 0.0035 1.0000
13.500 1.2509 0.05443 0.04954 -0.0322 0.0035 1.0000
13.750 1.2605 0.05630 0.05159 -0.0299 0.0036 1.0000
14.000 1.0653 0.05376 0.04955 -0.0123 0.0035 1.0000
14.250 1.0681 0.05650 0.05240 -0.0110 0.0036 1.0000
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