MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.64 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409-il-1000000.txt Download as CSV file: xf-ma409-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4269 0.02887 0.02563 -0.0954 0.7470 0.0070
-8.500 -0.4053 0.02355 0.01978 -0.0991 0.7465 0.0071
-8.250 -0.3820 0.02006 0.01584 -0.1007 0.7457 0.0072
-8.000 -0.3567 0.01793 0.01338 -0.1013 0.7445 0.0071
-7.750 -0.3312 0.01591 0.01104 -0.1016 0.7430 0.0071
-7.500 -0.3057 0.01383 0.00863 -0.1019 0.7417 0.0074
-7.250 -0.2791 0.01266 0.00727 -0.1020 0.7409 0.0080
-7.000 -0.2519 0.01199 0.00648 -0.1020 0.7404 0.0087
-6.750 -0.2244 0.01139 0.00576 -0.1020 0.7397 0.0094
-6.500 -0.1968 0.01085 0.00510 -0.1019 0.7387 0.0100
-6.250 -0.1691 0.01039 0.00453 -0.1019 0.7378 0.0106
-5.750 -0.1134 0.00931 0.00319 -0.1018 0.7363 0.0132
-5.500 -0.0854 0.00891 0.00272 -0.1017 0.7353 0.0155
-5.250 -0.0573 0.00864 0.00237 -0.1017 0.7341 0.0176
-5.000 -0.0295 0.00826 0.00216 -0.1016 0.7325 0.0476
-4.750 -0.0015 0.00820 0.00212 -0.1016 0.7307 0.0575
-4.500 0.0267 0.00825 0.00216 -0.1016 0.7292 0.0601
-4.250 0.0546 0.00805 0.00194 -0.1016 0.7278 0.0651
-4.000 0.0827 0.00796 0.00185 -0.1016 0.7264 0.0687
-3.750 0.1108 0.00794 0.00179 -0.1015 0.7248 0.0721
-3.500 0.1389 0.00787 0.00169 -0.1015 0.7232 0.0751
-3.250 0.1669 0.00769 0.00154 -0.1015 0.7216 0.0812
-3.000 0.1951 0.00758 0.00143 -0.1015 0.7200 0.0849
-2.750 0.2232 0.00748 0.00133 -0.1015 0.7181 0.0888
-2.500 0.2513 0.00735 0.00123 -0.1015 0.7161 0.0998
-2.250 0.2792 0.00717 0.00118 -0.1016 0.7137 0.1373
-2.000 0.3069 0.00702 0.00115 -0.1016 0.7102 0.1836
-1.750 0.3347 0.00674 0.00111 -0.1016 0.7057 0.2547
-1.500 0.3625 0.00661 0.00108 -0.1016 0.7005 0.2971
-1.250 0.3903 0.00650 0.00106 -0.1016 0.6959 0.3298
-1.000 0.4184 0.00635 0.00103 -0.1016 0.6888 0.3652
-0.750 0.4464 0.00615 0.00102 -0.1017 0.6783 0.4257
-0.500 0.4708 0.00623 0.00089 -0.1010 0.5843 0.4700
-0.250 0.4965 0.00622 0.00104 -0.1008 0.5696 0.5573
0.000 0.5164 0.00549 0.00121 -0.0990 0.5628 0.8926
0.250 0.5480 0.00547 0.00127 -0.0998 0.5546 1.0000
0.500 0.5755 0.00557 0.00136 -0.0997 0.5460 1.0000
0.750 0.6029 0.00568 0.00143 -0.0996 0.5357 1.0000
1.000 0.6306 0.00575 0.00147 -0.0995 0.5123 1.0000
1.250 0.6572 0.00594 0.00149 -0.0993 0.4681 1.0000
1.500 0.6822 0.00629 0.00162 -0.0988 0.4162 1.0000
1.750 0.7058 0.00681 0.00182 -0.0982 0.3438 1.0000
2.000 0.7314 0.00712 0.00199 -0.0978 0.3120 1.0000
2.250 0.7533 0.00789 0.00227 -0.0970 0.2037 1.0000
2.500 0.7739 0.00889 0.00270 -0.0959 0.0892 1.0000
2.750 0.7965 0.00972 0.00318 -0.0950 0.0172 1.0000
3.000 0.8227 0.00999 0.00351 -0.0947 0.0154 1.0000
3.250 0.8485 0.01033 0.00390 -0.0943 0.0136 1.0000
3.500 0.8731 0.01088 0.00454 -0.0936 0.0113 1.0000
3.750 0.8972 0.01151 0.00525 -0.0928 0.0103 1.0000
4.000 0.9223 0.01194 0.00571 -0.0923 0.0099 1.0000
4.250 0.9469 0.01244 0.00629 -0.0917 0.0094 1.0000
4.500 0.9709 0.01302 0.00692 -0.0910 0.0087 1.0000
4.750 0.9943 0.01367 0.00762 -0.0902 0.0080 1.0000
5.000 1.0169 0.01444 0.00844 -0.0892 0.0075 1.0000
5.250 1.0383 0.01543 0.00949 -0.0881 0.0072 1.0000
5.500 1.0592 0.01659 0.01073 -0.0867 0.0071 1.0000
5.750 1.0801 0.01780 0.01200 -0.0856 0.0068 1.0000
6.000 1.0991 0.01994 0.01421 -0.0842 0.0064 1.0000
6.250 1.1207 0.02168 0.01607 -0.0831 0.0064 1.0000
6.500 1.1421 0.02350 0.01803 -0.0819 0.0064 1.0000
6.750 1.1623 0.02566 0.02037 -0.0807 0.0064 1.0000
7.000 1.1791 0.02885 0.02382 -0.0789 0.0063 1.0000
7.250 1.1873 0.03421 0.02963 -0.0758 0.0062 1.0000
7.500 1.1976 0.03611 0.03188 -0.0731 0.0061 1.0000
7.750 1.2123 0.03725 0.03325 -0.0711 0.0058 1.0000
9.500 1.0451 0.05725 0.05486 -0.0355 0.0062 1.0000
9.750 1.0218 0.06167 0.05942 -0.0343 0.0062 1.0000
10.000 0.9978 0.06683 0.06470 -0.0343 0.0062 1.0000
10.250 0.9735 0.07256 0.07054 -0.0351 0.0062 1.0000
10.500 0.9489 0.07913 0.07723 -0.0374 0.0062 1.0000
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Polar data table (+)
Polar graphs
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