MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 100,000 Max Cl/Cd: 61.88 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409-il-100000.txt Download as CSV file: xf-ma409-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4259 0.09809 0.09342 -0.0258 1.0000 0.0858
-8.750 -0.4407 0.09691 0.09240 -0.0283 1.0000 0.0867
-8.500 -0.4463 0.09446 0.09003 -0.0352 1.0000 0.0872
-8.250 -0.4390 0.08914 0.08476 -0.0294 1.0000 0.0885
-8.000 -0.4312 0.08577 0.08140 -0.0260 1.0000 0.0905
-7.750 -0.4280 0.08287 0.07854 -0.0256 1.0000 0.0928
-7.500 -0.4261 0.07986 0.07557 -0.0268 1.0000 0.0958
-7.250 -0.4188 0.07519 0.07081 -0.0447 1.0000 0.1010
-7.000 -0.4167 0.07138 0.06712 -0.0383 1.0000 0.1022
-6.750 -0.4113 0.06861 0.06439 -0.0350 1.0000 0.1042
-6.500 -0.4030 0.06556 0.06130 -0.0352 1.0000 0.1078
-6.250 -0.3843 0.05986 0.05542 -0.0447 1.0000 0.1159
-6.000 -0.3392 0.04044 0.03499 -0.0608 1.0000 0.0587
-5.750 -0.3095 0.03470 0.02840 -0.0646 1.0000 0.0599
-5.500 -0.2919 0.03314 0.02701 -0.0643 1.0000 0.0662
-5.250 -0.2563 0.02796 0.02093 -0.0674 1.0000 0.0686
-5.000 -0.2213 0.02431 0.01649 -0.0693 1.0000 0.0775
-4.750 -0.1919 0.02284 0.01464 -0.0701 1.0000 0.1030
-4.500 -0.1667 0.02239 0.01404 -0.0700 1.0000 0.1264
-4.250 -0.1440 0.02218 0.01391 -0.0699 1.0000 0.1481
-4.000 -0.1147 0.02116 0.01243 -0.0702 1.0000 0.1541
-3.750 -0.0861 0.02019 0.01122 -0.0705 1.0000 0.1587
-3.500 -0.0591 0.01956 0.01049 -0.0706 1.0000 0.1654
-3.250 -0.0319 0.01898 0.00982 -0.0707 1.0000 0.1741
-3.000 -0.0045 0.01851 0.00924 -0.0708 1.0000 0.1828
-2.750 0.0232 0.01799 0.00875 -0.0710 1.0000 0.1934
-2.500 0.0509 0.01758 0.00840 -0.0712 1.0000 0.2104
-2.250 0.0793 0.01718 0.00822 -0.0716 1.0000 0.2445
-2.000 0.1116 0.01643 0.00814 -0.0728 1.0000 0.3774
-1.750 0.1445 0.01550 0.00810 -0.0738 1.0000 0.6111
-1.500 0.1520 0.01482 0.00803 -0.0693 1.0000 1.0000
-1.250 0.1776 0.01511 0.00808 -0.0694 1.0000 1.0000
-1.000 0.2029 0.01542 0.00822 -0.0694 1.0000 1.0000
-0.750 0.2356 0.01577 0.00843 -0.0709 0.9969 1.0000
-0.500 0.2793 0.01615 0.00867 -0.0745 0.9891 1.0000
-0.250 0.3264 0.01654 0.00896 -0.0787 0.9816 1.0000
0.000 0.3655 0.01682 0.00919 -0.0813 0.9728 1.0000
0.250 0.4055 0.01708 0.00945 -0.0840 0.9639 1.0000
0.500 0.4520 0.01729 0.00967 -0.0879 0.9559 1.0000
0.750 0.4882 0.01743 0.00985 -0.0897 0.9447 1.0000
1.000 0.5267 0.01751 0.01000 -0.0917 0.9333 1.0000
1.250 0.5674 0.01747 0.01009 -0.0940 0.9207 1.0000
1.500 0.6110 0.01719 0.00994 -0.0965 0.9059 1.0000
1.750 0.6571 0.01665 0.00955 -0.0989 0.8900 1.0000
2.000 0.6994 0.01599 0.00910 -0.1003 0.8739 1.0000
2.250 0.7307 0.01554 0.00881 -0.0998 0.8524 1.0000
2.500 0.7667 0.01487 0.00831 -0.0997 0.8299 1.0000
2.750 0.8013 0.01425 0.00782 -0.0991 0.8001 1.0000
3.000 0.8367 0.01376 0.00722 -0.0978 0.7465 1.0000
3.250 0.8530 0.01396 0.00747 -0.0946 0.6720 1.0000
3.500 0.8731 0.01411 0.00693 -0.0913 0.5759 1.0000
3.750 0.8917 0.01505 0.00762 -0.0891 0.4974 1.0000
4.000 0.9066 0.01588 0.00799 -0.0863 0.3826 1.0000
4.250 0.9143 0.01819 0.00888 -0.0830 0.1615 1.0000
4.500 0.9272 0.02072 0.01067 -0.0805 0.0680 1.0000
4.750 0.9463 0.02208 0.01204 -0.0788 0.0551 1.0000
5.000 0.9641 0.02356 0.01356 -0.0770 0.0495 1.0000
5.250 0.9823 0.02528 0.01534 -0.0750 0.0472 1.0000
5.500 1.0044 0.02711 0.01725 -0.0735 0.0457 1.0000
5.750 1.0300 0.02934 0.01958 -0.0725 0.0449 1.0000
6.000 1.0571 0.03190 0.02234 -0.0717 0.0443 1.0000
6.250 1.0815 0.03429 0.02505 -0.0707 0.0422 1.0000
6.500 1.1040 0.03701 0.02808 -0.0695 0.0410 1.0000
6.750 1.1234 0.04088 0.03258 -0.0674 0.0429 1.0000
7.000 1.1385 0.04520 0.03743 -0.0651 0.0452 1.0000
7.250 1.1507 0.05015 0.04273 -0.0632 0.0474 1.0000
7.500 1.1539 0.05530 0.04887 -0.0590 0.0546 1.0000
8.250 1.0389 0.06532 0.06072 -0.0394 0.0781 1.0000
8.500 1.0085 0.06999 0.06558 -0.0362 0.0794 1.0000
8.750 0.9801 0.07450 0.07023 -0.0345 0.0790 1.0000
9.000 0.9530 0.07942 0.07525 -0.0343 0.0779 1.0000
9.250 0.9273 0.08504 0.08094 -0.0354 0.0769 1.0000
9.500 0.9019 0.09148 0.08744 -0.0378 0.0762 1.0000
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Polar data table (+)
Polar graphs
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