MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 50,000 Max Cl/Cd: 42.94 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409-il-50000.txt Download as CSV file: xf-ma409-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MA409 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4382 0.10632 0.09973 -0.0199 1.0000 0.1838
-8.750 -0.4207 0.10101 0.09441 -0.0181 1.0000 0.1943
-8.500 -0.4411 0.10112 0.09471 -0.0194 1.0000 0.1979
-8.250 -0.4234 0.09584 0.08941 -0.0168 1.0000 0.2081
-8.000 -0.4318 0.09387 0.08760 -0.0178 1.0000 0.2137
-7.750 -0.4286 0.09108 0.08481 -0.0172 1.0000 0.2244
-7.500 -0.4218 0.08735 0.08113 -0.0156 1.0000 0.2328
-7.250 -0.4246 0.08488 0.07876 -0.0168 1.0000 0.2424
-7.000 -0.4260 0.08271 0.07667 -0.0189 1.0000 0.2545
-6.750 -0.4225 0.07993 0.07395 -0.0194 1.0000 0.2682
-6.500 -0.4168 0.07656 0.07062 -0.0180 1.0000 0.2826
-6.250 -0.4090 0.07303 0.06713 -0.0129 1.0000 0.3031
-6.000 -0.4062 0.07028 0.06445 -0.0122 1.0000 0.3270
-5.750 -0.4020 0.06760 0.06181 -0.0114 1.0000 0.3533
-5.500 -0.3964 0.06478 0.05902 -0.0100 1.0000 0.3807
-5.250 -0.2822 0.04300 0.03553 -0.0589 1.0000 0.1536
-5.000 -0.2531 0.03857 0.03071 -0.0616 1.0000 0.1643
-4.750 -0.2252 0.03535 0.02712 -0.0632 1.0000 0.1895
-4.500 -0.1945 0.03258 0.02382 -0.0650 1.0000 0.2134
-4.250 -0.1643 0.03021 0.02101 -0.0661 1.0000 0.2228
-4.000 -0.1327 0.02809 0.01834 -0.0674 1.0000 0.2293
-3.750 -0.1045 0.02682 0.01676 -0.0679 1.0000 0.2428
-3.500 -0.0752 0.02551 0.01510 -0.0684 1.0000 0.2512
-3.250 -0.0463 0.02439 0.01375 -0.0687 1.0000 0.2608
-3.000 -0.0177 0.02350 0.01265 -0.0690 1.0000 0.2757
-2.750 0.0097 0.02280 0.01183 -0.0690 1.0000 0.3006
-2.500 0.0391 0.02204 0.01100 -0.0692 1.0000 0.3346
-2.250 0.0694 0.02107 0.01026 -0.0694 1.0000 0.4051
-2.000 0.0961 0.01848 0.00936 -0.0679 1.0000 0.6916
-1.750 0.1094 0.01800 0.00873 -0.0651 1.0000 1.0000
-1.500 0.1356 0.01827 0.00854 -0.0652 1.0000 1.0000
-1.250 0.1608 0.01857 0.00852 -0.0652 1.0000 1.0000
-1.000 0.1856 0.01888 0.00860 -0.0652 1.0000 1.0000
-0.750 0.2100 0.01922 0.00875 -0.0651 1.0000 1.0000
-0.500 0.2341 0.01959 0.00895 -0.0650 1.0000 1.0000
-0.250 0.2580 0.01998 0.00923 -0.0649 1.0000 1.0000
0.000 0.2816 0.02040 0.00956 -0.0648 1.0000 1.0000
0.250 0.3049 0.02086 0.00996 -0.0648 1.0000 1.0000
0.500 0.3278 0.02136 0.01044 -0.0647 1.0000 1.0000
0.750 0.3503 0.02192 0.01101 -0.0647 1.0000 1.0000
1.000 0.3721 0.02256 0.01167 -0.0647 1.0000 1.0000
1.250 0.3931 0.02329 0.01246 -0.0648 1.0000 1.0000
1.500 0.4128 0.02419 0.01342 -0.0651 1.0000 1.0000
1.750 0.4305 0.02530 0.01463 -0.0654 1.0000 1.0000
2.000 0.4808 0.02677 0.01631 -0.0721 0.9840 1.0000
2.250 0.5430 0.02800 0.01778 -0.0802 0.9577 1.0000
2.500 0.5993 0.02890 0.01895 -0.0866 0.9308 1.0000
2.750 0.6593 0.02924 0.01968 -0.0926 0.9015 1.0000
3.000 0.7102 0.02894 0.01974 -0.0956 0.8663 1.0000
3.250 0.7713 0.02778 0.01905 -0.0988 0.8344 1.0000
3.500 0.8231 0.02659 0.01838 -0.1000 0.8050 1.0000
3.750 0.8686 0.02542 0.01765 -0.0997 0.7715 1.0000
4.000 0.9117 0.02290 0.01536 -0.0950 0.7111 1.0000
4.250 0.9161 0.02235 0.01495 -0.0883 0.6316 1.0000
4.500 0.9409 0.02191 0.01373 -0.0827 0.5276 1.0000
4.750 0.9411 0.02290 0.01432 -0.0765 0.3843 1.0000
5.000 0.9343 0.02734 0.01645 -0.0711 0.1513 1.0000
5.250 0.9528 0.02999 0.01872 -0.0691 0.1127 1.0000
5.500 0.9789 0.03242 0.02103 -0.0678 0.0986 1.0000
5.750 1.0113 0.03496 0.02377 -0.0671 0.0904 1.0000
6.000 1.0410 0.03799 0.02689 -0.0667 0.0837 1.0000
6.250 1.0669 0.04087 0.03017 -0.0657 0.0787 1.0000
6.500 1.0913 0.04444 0.03428 -0.0644 0.0777 1.0000
6.750 1.1104 0.04847 0.03891 -0.0627 0.0782 1.0000
7.000 1.1240 0.05290 0.04395 -0.0605 0.0798 1.0000
7.250 1.1335 0.05758 0.04916 -0.0584 0.0818 1.0000
7.500 1.1406 0.06248 0.05446 -0.0564 0.0839 1.0000
7.750 1.1549 0.06826 0.06035 -0.0556 0.0862 1.0000
8.000 1.1260 0.07281 0.06597 -0.0516 0.0910 1.0000
8.250 1.1113 0.07836 0.07185 -0.0500 0.0944 1.0000
8.500 1.1253 0.08448 0.07798 -0.0496 0.0995 1.0000
8.750 1.0828 0.08884 0.08272 -0.0481 0.1011 1.0000
9.000 1.0456 0.09467 0.08869 -0.0494 0.1024 1.0000
9.250 1.0107 0.10287 0.09695 -0.0548 0.1045 1.0000
9.500 0.9951 0.11136 0.10542 -0.0598 0.1095 1.0000
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Polar data table (+)
Polar graphs
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