FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 100,000 Max Cl/Cd: 54.8 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w127-il-100000-n5.txt Download as CSV file: xf-fx84w127-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-127
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3320 0.10074 0.09582 -0.0524 1.0000 0.0356
-10.250 -0.3365 0.09672 0.09188 -0.0539 1.0000 0.0357
-10.000 -0.3458 0.09329 0.08855 -0.0543 1.0000 0.0358
-9.750 -0.3450 0.08832 0.08362 -0.0581 0.9893 0.0357
-9.500 -0.3390 0.08219 0.07750 -0.0643 0.9785 0.0356
-9.250 -0.3362 0.07483 0.07014 -0.0722 0.9676 0.0354
-9.000 -0.3395 0.06506 0.06033 -0.0840 0.9542 0.0351
-8.750 -0.3551 0.05654 0.05160 -0.0925 0.9370 0.0347
-8.500 -0.3692 0.05010 0.04482 -0.0960 0.9227 0.0347
-8.250 -0.3781 0.04462 0.03884 -0.0970 0.9108 0.0350
-8.000 -0.3811 0.03981 0.03338 -0.0966 0.9003 0.0357
-7.750 -0.3719 0.03725 0.03048 -0.0958 0.8913 0.0370
-7.500 -0.3527 0.03595 0.02905 -0.0956 0.8849 0.0385
-7.250 -0.3375 0.03398 0.02676 -0.0947 0.8768 0.0399
-7.000 -0.3204 0.03160 0.02391 -0.0940 0.8704 0.0413
-6.750 -0.3020 0.02950 0.02133 -0.0930 0.8634 0.0430
-6.500 -0.2811 0.02797 0.01949 -0.0924 0.8569 0.0454
-6.250 -0.2573 0.02704 0.01845 -0.0920 0.8521 0.0480
-6.000 -0.2355 0.02589 0.01705 -0.0912 0.8446 0.0504
-5.750 -0.2108 0.02474 0.01556 -0.0906 0.8394 0.0537
-5.500 -0.1875 0.02388 0.01471 -0.0902 0.8336 0.0572
-5.250 -0.1635 0.02310 0.01382 -0.0896 0.8273 0.0610
-5.000 -0.1378 0.02227 0.01277 -0.0890 0.8227 0.0657
-4.750 -0.1146 0.02167 0.01221 -0.0885 0.8163 0.0709
-4.500 -0.0898 0.02106 0.01145 -0.0879 0.8106 0.0769
-4.250 -0.0645 0.02043 0.01084 -0.0875 0.8064 0.0845
-4.000 -0.0411 0.01998 0.01032 -0.0868 0.7995 0.0928
-3.750 -0.0162 0.01952 0.00984 -0.0864 0.7942 0.1044
-3.500 0.0095 0.01902 0.00933 -0.0859 0.7901 0.1184
-3.250 0.0328 0.01869 0.00905 -0.0853 0.7829 0.1365
-3.000 0.0580 0.01825 0.00869 -0.0849 0.7779 0.1620
-2.750 0.0831 0.01782 0.00837 -0.0845 0.7730 0.1992
-2.500 0.1063 0.01743 0.00820 -0.0839 0.7663 0.2550
-2.250 0.1304 0.01682 0.00795 -0.0834 0.7617 0.3497
-2.000 0.1513 0.01618 0.00791 -0.0822 0.7561 0.5011
-1.750 0.1705 0.01582 0.00809 -0.0799 0.7500 0.6530
-1.500 0.1928 0.01569 0.00812 -0.0777 0.7457 0.7456
-1.250 0.2143 0.01575 0.00822 -0.0758 0.7398 0.8046
-1.000 0.2376 0.01581 0.00825 -0.0741 0.7341 0.8487
-0.750 0.2657 0.01578 0.00813 -0.0733 0.7300 0.8855
-0.500 0.2969 0.01586 0.00815 -0.0735 0.7240 0.9172
-0.250 0.3368 0.01588 0.00807 -0.0755 0.7187 0.9452
0.000 0.3937 0.01578 0.00782 -0.0809 0.7149 0.9726
0.250 0.4524 0.01573 0.00766 -0.0872 0.7094 0.9921
0.500 0.4864 0.01575 0.00760 -0.0889 0.7034 1.0000
0.750 0.5071 0.01574 0.00748 -0.0878 0.6988 1.0000
1.000 0.5237 0.01595 0.00766 -0.0862 0.6914 1.0000
1.250 0.5440 0.01601 0.00765 -0.0849 0.6859 1.0000
1.500 0.5646 0.01612 0.00768 -0.0837 0.6803 1.0000
1.750 0.5836 0.01631 0.00785 -0.0824 0.6734 1.0000
2.000 0.6074 0.01635 0.00781 -0.0816 0.6686 1.0000
2.250 0.6274 0.01659 0.00805 -0.0805 0.6616 1.0000
2.500 0.6510 0.01672 0.00814 -0.0798 0.6559 1.0000
2.750 0.6763 0.01682 0.00820 -0.0793 0.6509 1.0000
3.000 0.6978 0.01710 0.00849 -0.0785 0.6436 1.0000
3.250 0.7243 0.01718 0.00853 -0.0782 0.6387 1.0000
3.500 0.7470 0.01745 0.00883 -0.0775 0.6318 1.0000
3.750 0.7720 0.01761 0.00901 -0.0771 0.6257 1.0000
4.000 0.7982 0.01774 0.00913 -0.0768 0.6200 1.0000
4.250 0.8209 0.01802 0.00946 -0.0761 0.6124 1.0000
4.500 0.8492 0.01806 0.00950 -0.0760 0.6072 1.0000
4.750 0.8702 0.01843 0.00996 -0.0752 0.5987 1.0000
5.000 0.8977 0.01851 0.01005 -0.0750 0.5929 1.0000
5.250 0.9196 0.01885 0.01048 -0.0743 0.5848 1.0000
5.500 0.9462 0.01897 0.01065 -0.0740 0.5783 1.0000
5.750 0.9684 0.01929 0.01106 -0.0732 0.5699 1.0000
6.000 0.9952 0.01938 0.01118 -0.0730 0.5626 1.0000
6.250 1.0162 0.01971 0.01163 -0.0720 0.5528 1.0000
6.500 1.0424 0.01981 0.01177 -0.0716 0.5447 1.0000
6.750 1.0639 0.02011 0.01218 -0.0707 0.5347 1.0000
7.000 1.0860 0.02039 0.01258 -0.0698 0.5250 1.0000
7.250 1.1113 0.02051 0.01275 -0.0693 0.5154 1.0000
7.500 1.1315 0.02071 0.01302 -0.0680 0.5013 1.0000
7.750 1.1469 0.02096 0.01335 -0.0660 0.4818 1.0000
8.000 1.1618 0.02120 0.01362 -0.0639 0.4594 1.0000
8.250 1.1753 0.02157 0.01398 -0.0617 0.4371 1.0000
8.500 1.1870 0.02205 0.01447 -0.0593 0.4142 1.0000
8.750 1.1951 0.02264 0.01504 -0.0565 0.3904 1.0000
9.000 1.2006 0.02340 0.01573 -0.0534 0.3642 1.0000
9.250 1.2042 0.02437 0.01662 -0.0504 0.3353 1.0000
9.500 1.2055 0.02561 0.01776 -0.0475 0.3022 1.0000
9.750 1.2036 0.02717 0.01914 -0.0446 0.2668 1.0000
10.000 1.1996 0.02905 0.02083 -0.0419 0.2310 1.0000
10.250 1.1943 0.03123 0.02281 -0.0395 0.1958 1.0000
10.500 1.1886 0.03362 0.02501 -0.0374 0.1635 1.0000
10.750 1.1832 0.03617 0.02739 -0.0355 0.1345 1.0000
11.000 1.1794 0.03873 0.02982 -0.0340 0.1117 1.0000
11.250 1.1762 0.04134 0.03235 -0.0327 0.0959 1.0000
11.500 1.1746 0.04392 0.03491 -0.0316 0.0842 1.0000
11.750 1.1745 0.04644 0.03746 -0.0307 0.0755 1.0000
12.000 1.1725 0.04921 0.04021 -0.0299 0.0694 1.0000
12.250 1.1744 0.05168 0.04279 -0.0293 0.0635 1.0000
12.500 1.1727 0.05460 0.04571 -0.0288 0.0592 1.0000
12.750 1.1755 0.05711 0.04833 -0.0283 0.0554 1.0000
13.000 1.1778 0.05973 0.05104 -0.0280 0.0520 1.0000
13.250 1.1781 0.06261 0.05395 -0.0278 0.0493 1.0000
13.500 1.1823 0.06511 0.05656 -0.0275 0.0466 1.0000
13.750 1.1872 0.06759 0.05916 -0.0273 0.0440 1.0000
14.000 1.1915 0.07013 0.06177 -0.0272 0.0419 1.0000
14.250 1.1953 0.07275 0.06441 -0.0270 0.0401 1.0000
14.500 1.2022 0.07507 0.06685 -0.0268 0.0382 1.0000
14.750 1.2088 0.07753 0.06947 -0.0267 0.0364 1.0000
15.000 1.2140 0.08016 0.07222 -0.0268 0.0347 1.0000
15.250 1.2196 0.08274 0.07487 -0.0268 0.0334 1.0000
15.500 1.2267 0.08511 0.07726 -0.0267 0.0323 1.0000
15.750 1.2327 0.08785 0.08017 -0.0268 0.0313 1.0000
16.000 1.2339 0.09137 0.08395 -0.0274 0.0301 1.0000
16.250 1.2346 0.09498 0.08777 -0.0282 0.0291 1.0000
16.500 1.2338 0.09881 0.09178 -0.0293 0.0282 1.0000
16.750 1.2325 0.10276 0.09589 -0.0306 0.0274 1.0000
17.000 1.2316 0.10670 0.09997 -0.0319 0.0268 1.0000
17.250 1.2305 0.11073 0.10414 -0.0333 0.0264 1.0000
17.500 1.2291 0.11483 0.10836 -0.0348 0.0259 1.0000
17.750 1.2245 0.11962 0.11329 -0.0368 0.0255 1.0000
18.000 1.2117 0.12619 0.12013 -0.0402 0.0254 1.0000
18.250 1.1965 0.13351 0.12772 -0.0444 0.0252 1.0000
18.500 1.1800 0.14139 0.13585 -0.0492 0.0252 1.0000
18.750 1.1608 0.15032 0.14502 -0.0549 0.0252 1.0000
19.000 1.1388 0.16057 0.15548 -0.0617 0.0252 1.0000
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