MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 500,000 Max Cl/Cd: 89.3 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409-il-500000-n5.txt Download as CSV file: xf-ma409-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3136 0.08532 0.08221 -0.0386 0.7422 0.0057
-10.250 -0.3139 0.08099 0.07790 -0.0397 0.7419 0.0056
-10.000 -0.3153 0.07638 0.07330 -0.0410 0.7415 0.0054
-9.750 -0.3172 0.07164 0.06859 -0.0423 0.7410 0.0053
-9.500 -0.3201 0.06673 0.06369 -0.0439 0.7406 0.0052
-9.250 -0.3247 0.06137 0.05836 -0.0459 0.7403 0.0051
-9.000 -0.3305 0.05578 0.05281 -0.0483 0.7398 0.0050
-8.500 -0.3955 0.03089 0.02712 -0.0947 0.7388 0.0041
-8.250 -0.3717 0.02500 0.02059 -0.0995 0.7382 0.0041
-8.000 -0.3472 0.02165 0.01675 -0.1014 0.7377 0.0042
-7.750 -0.3216 0.01935 0.01404 -0.1023 0.7372 0.0043
-7.500 -0.2955 0.01765 0.01204 -0.1028 0.7366 0.0044
-7.250 -0.2689 0.01632 0.01044 -0.1030 0.7357 0.0047
-7.000 -0.2420 0.01518 0.00906 -0.1032 0.7346 0.0049
-6.750 -0.2149 0.01422 0.00788 -0.1032 0.7333 0.0054
-6.500 -0.1875 0.01341 0.00689 -0.1032 0.7321 0.0058
-6.000 -0.1326 0.01196 0.00510 -0.1033 0.7296 0.0075
-5.750 -0.1047 0.01141 0.00441 -0.1033 0.7283 0.0084
-5.500 -0.0768 0.01097 0.00384 -0.1033 0.7272 0.0095
-5.250 -0.0488 0.01064 0.00338 -0.1032 0.7263 0.0107
-5.000 -0.0206 0.01025 0.00288 -0.1032 0.7253 0.0164
-4.750 0.0070 0.00981 0.00257 -0.1032 0.7240 0.0448
-4.500 0.0349 0.00969 0.00248 -0.1032 0.7224 0.0579
-4.250 0.0629 0.00965 0.00238 -0.1032 0.7206 0.0627
-4.000 0.0907 0.00951 0.00223 -0.1032 0.7191 0.0693
-3.750 0.1186 0.00946 0.00213 -0.1032 0.7174 0.0747
-3.500 0.1467 0.00935 0.00198 -0.1031 0.7159 0.0769
-3.250 0.1746 0.00918 0.00181 -0.1031 0.7138 0.0811
-3.000 0.2026 0.00904 0.00167 -0.1031 0.7113 0.0854
-2.750 0.2306 0.00894 0.00157 -0.1031 0.7090 0.0904
-2.500 0.2585 0.00881 0.00148 -0.1032 0.7067 0.1027
-2.250 0.2862 0.00868 0.00142 -0.1032 0.7043 0.1289
-2.000 0.3141 0.00856 0.00137 -0.1032 0.7017 0.1552
-1.750 0.3420 0.00838 0.00132 -0.1033 0.6980 0.1869
-1.500 0.3698 0.00818 0.00132 -0.1033 0.6942 0.2461
-1.250 0.3974 0.00806 0.00131 -0.1033 0.6893 0.2911
-1.000 0.4254 0.00788 0.00129 -0.1034 0.6756 0.3235
-0.750 0.4484 0.00793 0.00107 -0.1023 0.5809 0.3495
-0.500 0.4741 0.00805 0.00120 -0.1020 0.5683 0.3881
-0.250 0.5007 0.00807 0.00132 -0.1019 0.5601 0.4423
0.000 0.5273 0.00805 0.00145 -0.1017 0.5505 0.4969
0.250 0.5515 0.00758 0.00163 -0.1012 0.5410 0.7240
0.500 0.5780 0.00710 0.00168 -0.1005 0.5322 1.0000
0.750 0.6056 0.00718 0.00176 -0.1005 0.5229 1.0000
1.000 0.6332 0.00725 0.00185 -0.1004 0.5066 1.0000
1.250 0.6599 0.00739 0.00192 -0.1002 0.4798 1.0000
1.500 0.6847 0.00772 0.00204 -0.0997 0.4356 1.0000
1.750 0.7066 0.00838 0.00228 -0.0988 0.3449 1.0000
2.000 0.7305 0.00887 0.00253 -0.0982 0.2972 1.0000
2.250 0.7516 0.00972 0.00287 -0.0973 0.1856 1.0000
2.500 0.7725 0.01068 0.00332 -0.0964 0.0843 1.0000
2.750 0.7947 0.01153 0.00386 -0.0955 0.0173 1.0000
3.000 0.8203 0.01188 0.00427 -0.0950 0.0119 1.0000
3.250 0.8459 0.01223 0.00470 -0.0946 0.0103 1.0000
3.500 0.8708 0.01267 0.00521 -0.0940 0.0086 1.0000
3.750 0.8940 0.01341 0.00605 -0.0932 0.0070 1.0000
4.000 0.9182 0.01394 0.00667 -0.0925 0.0065 1.0000
4.250 0.9415 0.01462 0.00742 -0.0917 0.0059 1.0000
4.500 0.9639 0.01541 0.00829 -0.0907 0.0055 1.0000
4.750 0.9858 0.01625 0.00920 -0.0896 0.0052 1.0000
5.000 1.0082 0.01695 0.00993 -0.0888 0.0046 1.0000
5.250 1.0283 0.01807 0.01111 -0.0876 0.0041 1.0000
5.500 1.0496 0.01910 0.01230 -0.0864 0.0039 1.0000
5.750 1.0702 0.02039 0.01372 -0.0851 0.0036 1.0000
6.000 1.0908 0.02187 0.01535 -0.0837 0.0034 1.0000
6.250 1.1113 0.02353 0.01718 -0.0824 0.0032 1.0000
6.500 1.1314 0.02541 0.01926 -0.0810 0.0031 1.0000
6.750 1.1504 0.02754 0.02164 -0.0794 0.0030 1.0000
7.000 1.1674 0.03005 0.02444 -0.0776 0.0030 1.0000
7.250 1.1815 0.03299 0.02774 -0.0753 0.0030 1.0000
7.500 1.1919 0.03640 0.03153 -0.0726 0.0030 1.0000
7.750 1.1981 0.04009 0.03560 -0.0695 0.0031 1.0000
8.000 1.1996 0.04393 0.03982 -0.0661 0.0032 1.0000
8.250 1.1968 0.04782 0.04405 -0.0626 0.0033 1.0000
8.500 1.1899 0.05160 0.04812 -0.0590 0.0034 1.0000
8.750 1.1777 0.05493 0.05170 -0.0550 0.0034 1.0000
9.000 1.1611 0.05828 0.05525 -0.0512 0.0035 1.0000
9.250 1.1435 0.06198 0.05914 -0.0486 0.0034 1.0000
9.500 1.1246 0.06630 0.06364 -0.0475 0.0034 1.0000
9.750 1.1048 0.07145 0.06895 -0.0482 0.0035 1.0000
10.000 1.0849 0.07752 0.07518 -0.0507 0.0035 1.0000
10.250 1.0652 0.08496 0.08276 -0.0555 0.0036 1.0000
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Polar data table (+)
Polar graphs
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