FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-W-151 A (fx79w151a-il) Reynolds number: 50,000 Max Cl/Cd: 19.08 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79w151a-il-50000-n5.txt Download as CSV file: xf-fx79w151a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-W-151 A
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3355 0.11256 0.10575 -0.0542 1.0000 0.0665
-11.500 -0.3412 0.10782 0.10109 -0.0562 1.0000 0.0667
-11.250 -0.3484 0.10311 0.09646 -0.0580 1.0000 0.0669
-11.000 -0.3320 0.10340 0.09679 -0.0557 1.0000 0.0710
-10.750 -0.3377 0.10006 0.09355 -0.0563 1.0000 0.0726
-10.500 -0.3494 0.09643 0.09006 -0.0567 1.0000 0.0731
-10.250 -0.3666 0.09308 0.08685 -0.0565 1.0000 0.0738
-10.000 -0.3896 0.09011 0.08402 -0.0552 1.0000 0.0736
-9.750 -0.4173 0.08728 0.08135 -0.0537 1.0000 0.0735
-9.500 -0.4338 0.07755 0.07162 -0.0636 0.9874 0.0737
-9.250 -0.4612 0.06859 0.06254 -0.0720 0.9720 0.0734
-9.000 -0.4798 0.06183 0.05549 -0.0763 0.9580 0.0740
-8.750 -0.4919 0.05625 0.04951 -0.0780 0.9451 0.0756
-8.500 -0.5020 0.05134 0.04401 -0.0778 0.9326 0.0781
-8.250 -0.4900 0.04916 0.04162 -0.0777 0.9228 0.0822
-8.000 -0.4703 0.04684 0.03900 -0.0785 0.9155 0.0870
-7.750 -0.4675 0.04402 0.03560 -0.0764 0.9042 0.0912
-7.500 -0.4490 0.04265 0.03408 -0.0760 0.8959 0.0968
-7.250 -0.4311 0.04085 0.03188 -0.0754 0.8876 0.1031
-7.000 -0.4170 0.03917 0.02984 -0.0739 0.8784 0.1090
-6.750 -0.3929 0.03807 0.02852 -0.0738 0.8715 0.1175
-6.500 -0.3771 0.03684 0.02701 -0.0723 0.8621 0.1241
-6.250 -0.3514 0.03579 0.02568 -0.0722 0.8558 0.1341
-6.000 -0.3342 0.03501 0.02480 -0.0707 0.8466 0.1413
-5.750 -0.3070 0.03396 0.02339 -0.0708 0.8405 0.1523
-5.500 -0.2887 0.03343 0.02284 -0.0694 0.8316 0.1610
-5.250 -0.2603 0.03260 0.02184 -0.0696 0.8256 0.1721
-5.000 -0.2404 0.03208 0.02110 -0.0684 0.8170 0.1830
-4.750 -0.2113 0.03138 0.02029 -0.0686 0.8109 0.1942
-4.500 -0.1888 0.03093 0.01979 -0.0679 0.8032 0.2058
-4.250 -0.1610 0.03038 0.01915 -0.0679 0.7966 0.2189
-4.000 -0.1331 0.02989 0.01857 -0.0679 0.7902 0.2339
-3.750 -0.1091 0.02953 0.01816 -0.0675 0.7826 0.2501
-3.500 -0.0755 0.02889 0.01747 -0.0684 0.7781 0.2715
-3.250 -0.0587 0.02873 0.01736 -0.0668 0.7686 0.2928
-3.000 -0.0300 0.02812 0.01685 -0.0669 0.7637 0.3269
-2.750 -0.0157 0.02795 0.01685 -0.0649 0.7549 0.3644
-2.500 0.0071 0.02735 0.01657 -0.0638 0.7494 0.4325
-2.250 0.0212 0.02706 0.01669 -0.0613 0.7416 0.5200
-2.000 0.0490 0.02659 0.01677 -0.0602 0.7358 0.6561
-1.750 0.1288 0.02630 0.01673 -0.0677 0.7330 0.8179
-1.500 0.1928 0.02669 0.01693 -0.0737 0.7263 0.8936
-1.250 0.2586 0.02686 0.01683 -0.0801 0.7210 0.9441
-1.000 0.3370 0.02661 0.01626 -0.0893 0.7173 0.9837
-0.750 0.3791 0.02684 0.01632 -0.0933 0.7089 1.0000
-0.500 0.3973 0.02682 0.01612 -0.0919 0.7031 1.0000
-0.250 0.4054 0.02730 0.01649 -0.0893 0.6942 1.0000
0.000 0.4240 0.02737 0.01642 -0.0879 0.6884 1.0000
0.250 0.4335 0.02788 0.01683 -0.0855 0.6802 1.0000
0.500 0.4515 0.02805 0.01687 -0.0840 0.6740 1.0000
0.750 0.4641 0.02851 0.01722 -0.0818 0.6667 1.0000
1.000 0.4791 0.02887 0.01749 -0.0800 0.6598 1.0000
1.250 0.5027 0.02891 0.01740 -0.0791 0.6552 1.0000
1.500 0.5071 0.02979 0.01824 -0.0760 0.6459 1.0000
1.750 0.5330 0.02978 0.01812 -0.0754 0.6417 1.0000
2.000 0.5349 0.03084 0.01915 -0.0721 0.6324 1.0000
2.250 0.5591 0.03094 0.01917 -0.0713 0.6277 1.0000
2.500 0.5643 0.03192 0.02011 -0.0683 0.6194 1.0000
2.750 0.5835 0.03228 0.02042 -0.0670 0.6139 1.0000
3.000 0.6138 0.03217 0.02025 -0.0670 0.6106 1.0000
3.250 0.6072 0.03374 0.02182 -0.0628 0.6001 1.0000
3.500 0.6356 0.03374 0.02178 -0.0625 0.5965 1.0000
3.750 0.6289 0.03542 0.02345 -0.0585 0.5867 1.0000
4.000 0.6540 0.03559 0.02360 -0.0579 0.5824 1.0000
4.500 0.6683 0.03781 0.02582 -0.0530 0.5685 1.0000
4.750 0.6997 0.03772 0.02573 -0.0531 0.5656 1.0000
5.000 0.6777 0.04032 0.02833 -0.0478 0.5543 1.0000
5.250 0.7074 0.04036 0.02840 -0.0478 0.5512 1.0000
5.750 0.7109 0.04353 0.03160 -0.0427 0.5366 1.0000
6.250 0.7172 0.04715 0.03527 -0.0390 0.5220 1.0000
6.500 0.7431 0.04738 0.03554 -0.0385 0.5192 1.0000
6.750 0.7238 0.05119 0.03938 -0.0360 0.5075 1.0000
7.000 0.7522 0.05122 0.03950 -0.0356 0.5051 1.0000
7.250 0.7306 0.05548 0.04378 -0.0336 0.4935 1.0000
7.500 0.7570 0.05572 0.04409 -0.0331 0.4906 1.0000
8.000 0.7632 0.06022 0.04871 -0.0310 0.4764 1.0000
8.500 0.7693 0.06494 0.05359 -0.0292 0.4626 1.0000
8.750 0.7954 0.06526 0.05402 -0.0288 0.4600 1.0000
9.000 0.7777 0.06954 0.05834 -0.0278 0.4492 1.0000
9.250 0.8027 0.06993 0.05885 -0.0272 0.4458 1.0000
9.500 0.7901 0.07381 0.06280 -0.0265 0.4358 1.0000
9.750 0.8121 0.07445 0.06356 -0.0259 0.4316 1.0000
10.000 0.8052 0.07789 0.06709 -0.0254 0.4226 1.0000
10.250 0.8236 0.07885 0.06819 -0.0248 0.4174 1.0000
10.750 0.8378 0.08293 0.07250 -0.0238 0.4028 1.0000
11.250 0.8539 0.08679 0.07662 -0.0228 0.3878 1.0000
11.750 0.8731 0.09021 0.08035 -0.0217 0.3723 1.0000
12.000 0.8694 0.09342 0.08367 -0.0215 0.3620 1.0000
12.250 0.8952 0.09312 0.08357 -0.0205 0.3564 1.0000
12.500 0.8882 0.09672 0.08727 -0.0205 0.3449 1.0000
12.750 0.9162 0.09590 0.08671 -0.0193 0.3393 1.0000
14.250 0.9627 0.10359 0.09543 -0.0156 0.2692 1.0000
14.750 0.9794 0.10430 0.09650 -0.0142 0.2307 1.0000
15.000 0.9919 0.10403 0.09633 -0.0134 0.2026 1.0000
15.250 1.0095 0.10303 0.09515 -0.0121 0.1631 1.0000
15.500 1.0109 0.10509 0.09675 -0.0118 0.1282 1.0000
15.750 1.0032 0.10926 0.10063 -0.0125 0.1052 1.0000
16.000 0.9956 0.11358 0.10468 -0.0134 0.0895 1.0000
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Polar data table (+)
Polar graphs
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