FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 200,000 Max Cl/Cd: 71.88 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w121-il-200000.txt Download as CSV file: xf-fx77w121-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-121
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2078 0.09238 0.08802 -0.0213 0.5877 0.0362
-9.250 -0.2034 0.08914 0.08474 -0.0222 0.5852 0.0370
-9.000 -0.2003 0.08580 0.08137 -0.0232 0.5830 0.0378
-8.750 -0.1978 0.08235 0.07795 -0.0243 0.5801 0.0388
-8.500 -0.1963 0.07885 0.07446 -0.0256 0.5779 0.0398
-8.250 -0.1961 0.07531 0.07092 -0.0269 0.5756 0.0409
-8.000 -0.1983 0.07187 0.06750 -0.0288 0.5739 0.0423
-7.750 -0.2056 0.06851 0.06416 -0.0318 0.5726 0.0434
-7.500 -0.2112 0.06517 0.06083 -0.0344 0.5712 0.0437
-7.250 -0.2279 0.06206 0.05772 -0.0381 0.5702 0.0441
-7.000 -0.2321 0.05833 0.05393 -0.0401 0.5689 0.0443
-6.750 -0.2324 0.05443 0.04994 -0.0415 0.5673 0.0444
-6.250 -0.2556 0.05993 0.05494 -0.0463 0.5669 0.0458
-6.000 -0.2431 0.05765 0.05271 -0.0454 0.5643 0.0472
-5.750 -0.2308 0.05490 0.04989 -0.0453 0.5621 0.0483
-5.500 -0.2170 0.05245 0.04733 -0.0452 0.5599 0.0530
-5.250 -0.1996 0.05156 0.04572 -0.0448 0.5581 0.0576
-5.000 -0.1919 0.04517 0.03939 -0.0447 0.5563 0.0595
-4.750 -0.1750 0.04297 0.03715 -0.0441 0.5543 0.0615
-4.500 -0.1572 0.04089 0.03496 -0.0433 0.5525 0.0649
-4.250 -0.1414 0.03841 0.03193 -0.0416 0.5508 0.0733
-4.000 -0.1191 0.01518 0.00951 -0.0385 0.5477 0.0767
-3.750 -0.1023 0.01317 0.00707 -0.0370 0.5460 0.0878
-3.500 -0.0830 0.01140 0.00533 -0.0365 0.5441 0.0915
-3.250 -0.0598 0.02733 0.01951 -0.0350 0.5440 0.0603
-3.000 -0.0349 0.02445 0.01620 -0.0333 0.5424 0.0500
-2.750 -0.0087 0.02228 0.01348 -0.0318 0.5407 0.0475
-2.500 0.0179 0.02117 0.01213 -0.0311 0.5389 0.0487
-2.250 0.0444 0.02055 0.01144 -0.0307 0.5372 0.0531
-2.000 0.0718 0.01977 0.01052 -0.0302 0.5354 0.0559
-1.750 0.0989 0.01895 0.00962 -0.0298 0.5338 0.0588
-1.500 0.1244 0.01831 0.00906 -0.0293 0.5321 0.0654
-1.250 0.1501 0.01793 0.00863 -0.0287 0.5304 0.0706
-1.000 0.1741 0.01744 0.00818 -0.0278 0.5286 0.0799
-0.750 0.3471 0.01418 0.00752 -0.0579 0.5250 1.0000
-0.500 0.3718 0.01444 0.00760 -0.0574 0.5237 1.0000
-0.250 0.3964 0.01464 0.00774 -0.0569 0.5222 1.0000
0.000 0.4209 0.01487 0.00791 -0.0564 0.5204 1.0000
0.250 0.4455 0.01512 0.00811 -0.0559 0.5187 1.0000
0.500 0.4701 0.01537 0.00829 -0.0555 0.5168 1.0000
0.750 0.4948 0.01559 0.00843 -0.0549 0.5147 1.0000
1.000 0.5195 0.01582 0.00859 -0.0545 0.5129 1.0000
1.250 0.5444 0.01609 0.00879 -0.0540 0.5115 1.0000
1.500 0.5692 0.01638 0.00900 -0.0535 0.5099 1.0000
1.750 0.5936 0.01677 0.00934 -0.0530 0.5082 1.0000
2.000 0.6170 0.01714 0.00979 -0.0525 0.5055 1.0000
2.250 0.6409 0.01751 0.01017 -0.0521 0.5029 1.0000
2.500 0.6651 0.01785 0.01051 -0.0516 0.5006 1.0000
2.750 0.6895 0.01817 0.01083 -0.0511 0.4988 1.0000
3.000 0.7144 0.01842 0.01103 -0.0506 0.4968 1.0000
3.250 0.7393 0.01872 0.01128 -0.0501 0.4951 1.0000
3.500 0.7628 0.01922 0.01180 -0.0496 0.4930 1.0000
3.750 0.7842 0.01985 0.01258 -0.0491 0.4898 1.0000
4.000 0.8071 0.02029 0.01309 -0.0485 0.4866 1.0000
4.250 0.8317 0.02051 0.01330 -0.0480 0.4838 1.0000
4.500 0.8572 0.02065 0.01339 -0.0475 0.4816 1.0000
4.750 0.8828 0.02085 0.01355 -0.0470 0.4796 1.0000
5.000 0.9018 0.02167 0.01457 -0.0462 0.4753 1.0000
5.250 0.9235 0.02220 0.01520 -0.0456 0.4717 1.0000
5.500 0.9482 0.02236 0.01536 -0.0450 0.4688 1.0000
5.750 0.9746 0.02237 0.01537 -0.0446 0.4665 1.0000
6.000 1.0011 0.02248 0.01543 -0.0442 0.4644 1.0000
6.250 1.0164 0.02346 0.01668 -0.0430 0.4583 1.0000
6.500 1.0405 0.02360 0.01687 -0.0425 0.4548 1.0000
6.750 1.0672 0.02355 0.01684 -0.0420 0.4523 1.0000
7.000 1.0941 0.02358 0.01686 -0.0417 0.4502 1.0000
7.250 1.1082 0.02469 0.01822 -0.0404 0.4444 1.0000
7.500 1.1312 0.02491 0.01854 -0.0398 0.4405 1.0000
7.750 1.1584 0.02475 0.01842 -0.0394 0.4377 1.0000
8.000 1.1874 0.02451 0.01817 -0.0392 0.4354 1.0000
8.250 1.1994 0.02560 0.01954 -0.0376 0.4286 1.0000
8.500 1.2247 0.02551 0.01954 -0.0371 0.4247 1.0000
8.750 1.2537 0.02513 0.01920 -0.0368 0.4219 1.0000
9.000 1.2731 0.02541 0.01965 -0.0357 0.4161 1.0000
9.250 1.3053 0.02378 0.01801 -0.0353 0.4083 1.0000
9.500 1.3311 0.02245 0.01676 -0.0342 0.3975 1.0000
9.750 1.3573 0.02114 0.01552 -0.0332 0.3861 1.0000
10.000 1.3788 0.02026 0.01482 -0.0318 0.3697 1.0000
10.250 1.3995 0.01947 0.01403 -0.0303 0.3406 1.0000
10.500 1.4072 0.01982 0.01407 -0.0274 0.2898 1.0000
10.750 1.3937 0.02183 0.01568 -0.0227 0.2371 1.0000
11.000 1.3702 0.02429 0.01793 -0.0174 0.2006 1.0000
11.250 1.3459 0.02771 0.02127 -0.0148 0.1763 1.0000
11.500 1.3242 0.03231 0.02581 -0.0148 0.1525 1.0000
11.750 1.2986 0.03765 0.03100 -0.0152 0.1261 1.0000
12.000 1.2664 0.04367 0.03680 -0.0155 0.0954 1.0000
12.250 1.2511 0.04789 0.04096 -0.0155 0.0790 1.0000
12.500 1.2331 0.05241 0.04537 -0.0156 0.0604 1.0000
12.750 1.2089 0.05768 0.05047 -0.0158 0.0432 1.0000
13.000 1.1909 0.06260 0.05533 -0.0161 0.0340 1.0000
13.250 1.1830 0.06655 0.05938 -0.0164 0.0304 1.0000
13.500 1.1751 0.07058 0.06347 -0.0169 0.0281 1.0000
13.750 1.1652 0.07500 0.06796 -0.0175 0.0264 1.0000
14.000 1.1567 0.07931 0.07238 -0.0181 0.0245 1.0000
14.250 1.1532 0.08297 0.07614 -0.0186 0.0239 1.0000
14.500 1.1502 0.08660 0.07984 -0.0191 0.0219 1.0000
14.750 1.1486 0.08995 0.08329 -0.0195 0.0221 1.0000
15.000 1.1474 0.09317 0.08654 -0.0196 0.0211 1.0000
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Polar data table (+)
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