MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.83 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409-il-1000000-n5.txt Download as CSV file: xf-ma409-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4414 0.08661 0.08392 -0.0334 0.7068 0.0024
-9.750 -0.4510 0.07911 0.07646 -0.0377 0.7066 0.0024
-9.250 -0.4751 0.02671 0.02326 -0.0973 0.7068 0.0021
-9.000 -0.4520 0.02261 0.01869 -0.1002 0.7062 0.0022
-8.750 -0.4274 0.02017 0.01590 -0.1014 0.7053 0.0022
-8.500 -0.4035 0.01719 0.01245 -0.1026 0.7044 0.0024
-8.250 -0.3773 0.01623 0.01133 -0.1028 0.7034 0.0025
-8.000 -0.3507 0.01542 0.01038 -0.1030 0.7026 0.0027
-7.750 -0.3239 0.01444 0.00921 -0.1032 0.7020 0.0028
-7.500 -0.2970 0.01343 0.00800 -0.1033 0.7012 0.0030
-7.250 -0.2698 0.01258 0.00699 -0.1034 0.7004 0.0032
-7.000 -0.2423 0.01186 0.00613 -0.1034 0.6995 0.0034
-6.750 -0.2147 0.01129 0.00543 -0.1034 0.6984 0.0037
-6.500 -0.1870 0.01085 0.00489 -0.1034 0.6976 0.0039
-6.250 -0.1593 0.01019 0.00410 -0.1034 0.6968 0.0044
-6.000 -0.1315 0.00982 0.00365 -0.1034 0.6959 0.0049
-5.750 -0.1036 0.00953 0.00331 -0.1034 0.6950 0.0056
-5.500 -0.0757 0.00929 0.00302 -0.1034 0.6937 0.0063
-5.250 -0.0477 0.00892 0.00255 -0.1034 0.6920 0.0077
-5.000 -0.0198 0.00867 0.00223 -0.1034 0.6902 0.0095
-4.750 0.0083 0.00849 0.00198 -0.1034 0.6887 0.0117
-4.500 0.0363 0.00813 0.00172 -0.1034 0.6868 0.0345
-4.250 0.0645 0.00795 0.00160 -0.1035 0.6843 0.0485
-4.000 0.0926 0.00781 0.00149 -0.1035 0.6803 0.0575
-3.750 0.1208 0.00772 0.00140 -0.1035 0.6753 0.0616
-3.500 0.1483 0.00760 0.00114 -0.1034 0.6063 0.0660
-3.250 0.1743 0.00772 0.00110 -0.1031 0.5787 0.0709
-2.750 0.2294 0.00772 0.00100 -0.1029 0.5680 0.0754
-2.500 0.2572 0.00769 0.00095 -0.1029 0.5648 0.0789
-2.250 0.2849 0.00766 0.00091 -0.1028 0.5613 0.0844
-2.000 0.3124 0.00766 0.00091 -0.1028 0.5572 0.0913
-1.750 0.3401 0.00757 0.00090 -0.1028 0.5523 0.1176
-1.500 0.3677 0.00752 0.00091 -0.1028 0.5460 0.1443
-1.250 0.3953 0.00750 0.00092 -0.1027 0.5409 0.1634
-1.000 0.4232 0.00739 0.00093 -0.1028 0.5355 0.1978
-0.750 0.4508 0.00728 0.00097 -0.1029 0.5269 0.2586
-0.500 0.4787 0.00722 0.00098 -0.1029 0.5110 0.2891
-0.250 0.5060 0.00724 0.00099 -0.1029 0.4832 0.3128
0.000 0.5328 0.00732 0.00104 -0.1027 0.4601 0.3380
0.250 0.5597 0.00737 0.00112 -0.1026 0.4431 0.3725
0.500 0.5867 0.00738 0.00122 -0.1026 0.4263 0.4265
0.750 0.6126 0.00754 0.00133 -0.1023 0.3839 0.4606
1.000 0.6375 0.00755 0.00152 -0.1021 0.3433 0.5992
1.250 0.6597 0.00696 0.00171 -0.1009 0.3129 1.0000
1.500 0.6856 0.00723 0.00185 -0.1006 0.2766 1.0000
1.750 0.7078 0.00798 0.00215 -0.0998 0.1770 1.0000
2.000 0.7311 0.00862 0.00244 -0.0992 0.1013 1.0000
2.250 0.7538 0.00938 0.00284 -0.0984 0.0225 1.0000
2.500 0.7800 0.00964 0.00307 -0.0981 0.0122 1.0000
2.750 0.8064 0.00986 0.00333 -0.0979 0.0100 1.0000
3.000 0.8322 0.01019 0.00369 -0.0975 0.0074 1.0000
3.250 0.8583 0.01045 0.00397 -0.0972 0.0063 1.0000
3.500 0.8840 0.01075 0.00429 -0.0969 0.0055 1.0000
3.750 0.9094 0.01110 0.00467 -0.0965 0.0048 1.0000
4.000 0.9337 0.01165 0.00528 -0.0958 0.0042 1.0000
4.250 0.9586 0.01207 0.00576 -0.0953 0.0039 1.0000
4.500 0.9835 0.01247 0.00620 -0.0949 0.0035 1.0000
4.750 1.0084 0.01285 0.00660 -0.0944 0.0031 1.0000
5.000 1.0326 0.01333 0.00711 -0.0939 0.0028 1.0000
5.250 1.0555 0.01400 0.00783 -0.0931 0.0026 1.0000
5.500 1.0768 0.01491 0.00887 -0.0920 0.0024 1.0000
5.750 1.0993 0.01562 0.00966 -0.0911 0.0023 1.0000
6.000 1.1205 0.01651 0.01066 -0.0900 0.0022 1.0000
6.250 1.1407 0.01760 0.01187 -0.0887 0.0020 1.0000
6.500 1.1600 0.01891 0.01332 -0.0872 0.0019 1.0000
6.750 1.1786 0.02050 0.01508 -0.0856 0.0018 1.0000
7.000 1.1960 0.02259 0.01738 -0.0837 0.0017 1.0000
7.250 1.2112 0.02568 0.02079 -0.0814 0.0017 1.0000
7.500 1.2233 0.02943 0.02493 -0.0785 0.0017 1.0000
7.750 1.2359 0.03201 0.02778 -0.0763 0.0016 1.0000
8.000 1.2481 0.03407 0.03005 -0.0742 0.0016 1.0000
8.250 1.2590 0.03601 0.03219 -0.0722 0.0015 1.0000
8.500 1.2670 0.03811 0.03450 -0.0698 0.0014 1.0000
8.750 1.2723 0.04021 0.03680 -0.0673 0.0014 1.0000
9.000 1.2700 0.04315 0.04003 -0.0639 0.0014 1.0000
9.250 1.2578 0.04632 0.04343 -0.0594 0.0013 1.0000
9.500 1.2397 0.04969 0.04702 -0.0548 0.0013 1.0000
9.750 1.2212 0.05333 0.05086 -0.0513 0.0013 1.0000
10.000 1.2019 0.05747 0.05519 -0.0492 0.0013 1.0000
10.250 1.1825 0.06225 0.06016 -0.0488 0.0013 1.0000
10.500 1.1637 0.06782 0.06588 -0.0501 0.0013 1.0000
10.750 1.1440 0.07430 0.07251 -0.0529 0.0013 1.0000
11.000 1.1242 0.08270 0.08103 -0.0585 0.0013 1.0000
11.250 1.1022 0.09325 0.09172 -0.0659 0.0014 1.0000
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Polar data table (+)
Polar graphs
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