FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 50,000 Max Cl/Cd: 34.54 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w108-il-50000-n5.txt Download as CSV file: xf-fx83w108-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-108
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3685 0.10491 0.09771 -0.0460 1.0000 0.0658
-9.000 -0.3757 0.10218 0.09508 -0.0452 1.0000 0.0647
-8.750 -0.3858 0.09956 0.09257 -0.0441 1.0000 0.0638
-8.500 -0.3985 0.09707 0.09019 -0.0427 1.0000 0.0632
-8.250 -0.4142 0.09465 0.08789 -0.0411 1.0000 0.0624
-8.000 -0.4341 0.09217 0.08554 -0.0393 1.0000 0.0616
-7.500 -0.4963 0.08029 0.07387 -0.0450 1.0000 0.0579
-7.250 -0.4939 0.07434 0.06785 -0.0505 0.9966 0.0576
-7.000 -0.4838 0.06531 0.05847 -0.0620 0.9888 0.0579
-6.750 -0.4652 0.06288 0.05608 -0.0635 0.9836 0.0598
-6.500 -0.4465 0.05744 0.05034 -0.0697 0.9779 0.0609
-6.250 -0.4264 0.05209 0.04454 -0.0751 0.9719 0.0620
-6.000 -0.4001 0.04699 0.03884 -0.0802 0.9673 0.0630
-5.750 -0.3756 0.04328 0.03459 -0.0830 0.9621 0.0647
-5.500 -0.3452 0.04002 0.03062 -0.0861 0.9579 0.0686
-5.250 -0.3150 0.03747 0.02756 -0.0882 0.9542 0.0716
-5.000 -0.2895 0.03577 0.02564 -0.0888 0.9492 0.0744
-4.750 -0.2592 0.03428 0.02384 -0.0901 0.9451 0.0796
-4.500 -0.2262 0.03282 0.02203 -0.0916 0.9419 0.0856
-4.250 -0.2026 0.03180 0.02094 -0.0914 0.9367 0.0905
-4.000 -0.1735 0.03085 0.01973 -0.0920 0.9322 0.0994
-3.750 -0.1419 0.02997 0.01878 -0.0931 0.9286 0.1099
-3.500 -0.1145 0.02922 0.01799 -0.0935 0.9241 0.1234
-3.250 -0.0880 0.02853 0.01727 -0.0938 0.9190 0.1436
-3.000 -0.0556 0.02776 0.01670 -0.0954 0.9150 0.1843
-2.750 -0.0209 0.02718 0.01656 -0.0973 0.9119 0.2725
-2.500 -0.0005 0.02725 0.01674 -0.0963 0.9054 0.3448
-2.250 0.0277 0.02740 0.01689 -0.0965 0.9006 0.4036
-2.000 0.0591 0.02756 0.01707 -0.0972 0.8969 0.4585
-1.750 0.0777 0.02773 0.01727 -0.0956 0.8904 0.4966
-1.500 0.1052 0.02781 0.01730 -0.0956 0.8854 0.5330
-1.250 0.1374 0.02783 0.01728 -0.0964 0.8819 0.5648
-1.000 0.1578 0.02794 0.01740 -0.0952 0.8755 0.5900
-0.750 0.1851 0.02799 0.01745 -0.0953 0.8704 0.6188
-0.500 0.2173 0.02796 0.01745 -0.0961 0.8667 0.6520
-0.250 0.2371 0.02807 0.01764 -0.0948 0.8603 0.6868
0.000 0.2623 0.02804 0.01775 -0.0943 0.8550 0.7353
0.250 0.2954 0.02776 0.01773 -0.0949 0.8514 0.8311
0.500 0.3215 0.02796 0.01785 -0.0955 0.8439 1.0000
0.750 0.3530 0.02836 0.01804 -0.0968 0.8386 1.0000
1.000 0.3903 0.02867 0.01816 -0.0988 0.8348 1.0000
1.250 0.4067 0.02929 0.01866 -0.0975 0.8263 1.0000
1.500 0.4396 0.02965 0.01890 -0.0987 0.8214 1.0000
1.750 0.4623 0.03021 0.01938 -0.0984 0.8146 1.0000
2.000 0.4885 0.03069 0.01979 -0.0985 0.8081 1.0000
2.250 0.5243 0.03098 0.02004 -0.1000 0.8041 1.0000
2.500 0.5383 0.03175 0.02078 -0.0983 0.7946 1.0000
2.750 0.5718 0.03206 0.02108 -0.0994 0.7897 1.0000
3.000 0.5893 0.03276 0.02178 -0.0982 0.7807 1.0000
3.250 0.6212 0.03307 0.02213 -0.0989 0.7749 1.0000
3.500 0.6402 0.03374 0.02282 -0.0978 0.7657 1.0000
3.750 0.6722 0.03400 0.02313 -0.0984 0.7595 1.0000
4.000 0.6904 0.03467 0.02387 -0.0973 0.7495 1.0000
4.250 0.7257 0.03473 0.02402 -0.0981 0.7434 1.0000
4.500 0.7428 0.03537 0.02474 -0.0966 0.7319 1.0000
4.750 0.7843 0.03500 0.02452 -0.0979 0.7264 1.0000
5.000 0.8014 0.03553 0.02515 -0.0962 0.7135 1.0000
5.250 0.8227 0.03582 0.02556 -0.0950 0.7010 1.0000
5.500 0.8492 0.03574 0.02562 -0.0940 0.6889 1.0000
5.750 0.8854 0.03494 0.02503 -0.0938 0.6779 1.0000
6.000 0.9144 0.03431 0.02457 -0.0925 0.6629 1.0000
6.250 0.9348 0.03398 0.02439 -0.0903 0.6439 1.0000
6.500 0.9621 0.03304 0.02365 -0.0883 0.6237 1.0000
6.750 0.9861 0.03229 0.02306 -0.0861 0.6011 1.0000
7.000 1.0068 0.03175 0.02267 -0.0836 0.5745 1.0000
7.250 1.0224 0.03158 0.02262 -0.0807 0.5407 1.0000
7.500 1.0417 0.03120 0.02228 -0.0779 0.4950 1.0000
7.750 1.0642 0.03081 0.02163 -0.0753 0.4266 1.0000
8.000 1.0754 0.03154 0.02181 -0.0720 0.3475 1.0000
8.250 1.0756 0.03331 0.02307 -0.0686 0.2862 1.0000
8.500 1.0746 0.03538 0.02477 -0.0656 0.2398 1.0000
8.750 1.0752 0.03751 0.02660 -0.0630 0.2036 1.0000
9.000 1.0778 0.03962 0.02849 -0.0609 0.1770 1.0000
9.250 1.0844 0.04153 0.03032 -0.0590 0.1560 1.0000
9.500 1.0927 0.04340 0.03212 -0.0573 0.1400 1.0000
9.750 1.1028 0.04519 0.03388 -0.0558 0.1265 1.0000
10.000 1.1154 0.04689 0.03555 -0.0544 0.1155 1.0000
10.250 1.1320 0.04844 0.03711 -0.0531 0.1064 1.0000
10.500 1.1532 0.04984 0.03868 -0.0521 0.0974 1.0000
10.750 1.1763 0.05129 0.04008 -0.0514 0.0904 1.0000
11.000 1.2014 0.05289 0.04195 -0.0507 0.0838 1.0000
11.250 1.2244 0.05461 0.04354 -0.0502 0.0783 1.0000
11.500 1.2434 0.05684 0.04626 -0.0493 0.0740 1.0000
11.750 1.2595 0.05916 0.04882 -0.0484 0.0704 1.0000
12.000 1.2732 0.06135 0.05106 -0.0476 0.0673 1.0000
12.250 1.2824 0.06423 0.05419 -0.0465 0.0649 1.0000
12.500 1.2818 0.06762 0.05801 -0.0450 0.0630 1.0000
12.750 1.2796 0.07126 0.06202 -0.0436 0.0618 1.0000
13.000 1.2731 0.07521 0.06630 -0.0425 0.0608 1.0000
13.250 1.2628 0.07941 0.07081 -0.0416 0.0600 1.0000
13.500 1.2491 0.08399 0.07568 -0.0412 0.0594 1.0000
13.750 1.2323 0.08896 0.08092 -0.0413 0.0588 1.0000
14.000 1.2107 0.09477 0.08700 -0.0422 0.0586 1.0000
14.250 1.1822 0.10192 0.09442 -0.0445 0.0588 1.0000
14.500 1.1447 0.11129 0.10407 -0.0489 0.0596 1.0000
14.750 1.1003 0.12373 0.11671 -0.0564 0.0607 1.0000
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Polar data table (+)
Polar graphs
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