MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 50,000 Max Cl/Cd: 43.47 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409sm-il-50000.txt Download as CSV file: xf-ma409sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MA409 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4301 0.10104 0.09431 -0.0184 1.0000 0.2006
-7.250 -0.4169 0.09655 0.08983 -0.0167 1.0000 0.2106
-7.000 -0.4351 0.09654 0.09002 -0.0197 1.0000 0.2154
-6.750 -0.4212 0.09189 0.08538 -0.0164 1.0000 0.2273
-6.250 -0.4225 0.08677 0.08044 -0.0182 1.0000 0.2443
-6.000 -0.4148 0.08341 0.07711 -0.0164 1.0000 0.2556
-5.750 -0.4084 0.07994 0.07370 -0.0150 1.0000 0.2646
-5.500 -0.4049 0.07702 0.07085 -0.0151 1.0000 0.2764
-5.250 -0.4000 0.07408 0.06791 -0.0151 1.0000 0.2899
-5.000 -0.3937 0.07108 0.06495 -0.0147 1.0000 0.3047
-4.750 -0.3864 0.06812 0.06203 -0.0142 1.0000 0.3218
-4.500 -0.3792 0.06520 0.05915 -0.0144 1.0000 0.3440
-4.250 -0.2771 0.04648 0.03902 -0.0584 1.0000 0.1472
-4.000 -0.2461 0.04167 0.03379 -0.0619 1.0000 0.1437
-3.750 -0.2121 0.03679 0.02840 -0.0654 1.0000 0.1397
-3.500 -0.1748 0.03231 0.02316 -0.0687 1.0000 0.1398
-3.250 -0.1435 0.02979 0.02017 -0.0701 1.0000 0.1558
-3.000 -0.1101 0.02715 0.01702 -0.0712 1.0000 0.1705
-2.750 -0.0797 0.02548 0.01503 -0.0718 1.0000 0.2017
-2.500 -0.0513 0.02393 0.01343 -0.0718 1.0000 0.2372
-2.250 -0.0231 0.02279 0.01229 -0.0718 1.0000 0.2895
-2.000 0.0042 0.02189 0.01147 -0.0715 1.0000 0.3504
-1.750 0.0326 0.02102 0.01067 -0.0713 1.0000 0.4192
-1.500 0.0612 0.02001 0.00988 -0.0712 1.0000 0.5036
-1.250 0.0875 0.01856 0.00910 -0.0702 1.0000 0.6403
-1.000 0.0996 0.01728 0.00830 -0.0666 1.0000 1.0000
-0.750 0.1281 0.01753 0.00800 -0.0673 1.0000 1.0000
-0.500 0.1538 0.01781 0.00792 -0.0674 1.0000 1.0000
-0.250 0.1786 0.01812 0.00797 -0.0674 1.0000 1.0000
0.000 0.2029 0.01847 0.00807 -0.0674 1.0000 1.0000
0.250 0.2268 0.01885 0.00828 -0.0673 1.0000 1.0000
0.500 0.2502 0.01927 0.00857 -0.0673 1.0000 1.0000
0.750 0.2731 0.01974 0.00893 -0.0672 1.0000 1.0000
1.000 0.2956 0.02025 0.00937 -0.0672 1.0000 1.0000
1.250 0.3176 0.02082 0.00989 -0.0671 1.0000 1.0000
1.500 0.3391 0.02146 0.01050 -0.0671 1.0000 1.0000
1.750 0.3600 0.02216 0.01120 -0.0672 1.0000 1.0000
2.000 0.3802 0.02295 0.01200 -0.0672 1.0000 1.0000
2.250 0.3997 0.02384 0.01294 -0.0674 1.0000 1.0000
2.500 0.4184 0.02483 0.01398 -0.0676 1.0000 1.0000
2.750 0.4362 0.02594 0.01516 -0.0679 1.0000 1.0000
3.000 0.4767 0.02730 0.01665 -0.0726 0.9878 1.0000
3.250 0.5383 0.02855 0.01814 -0.0806 0.9628 1.0000
3.500 0.5958 0.02944 0.01928 -0.0871 0.9365 1.0000
3.750 0.6502 0.02998 0.02011 -0.0923 0.9091 1.0000
4.000 0.7026 0.03018 0.02069 -0.0964 0.8808 1.0000
4.250 0.7551 0.02995 0.02084 -0.0997 0.8519 1.0000
4.500 0.8103 0.02913 0.02048 -0.1022 0.8230 1.0000
4.750 0.8634 0.02778 0.01967 -0.1030 0.7933 1.0000
5.000 0.9030 0.02664 0.01896 -0.1015 0.7568 1.0000
5.250 0.9436 0.02346 0.01603 -0.0956 0.6943 1.0000
5.500 0.9604 0.02212 0.01452 -0.0883 0.6057 1.0000
5.750 0.9684 0.02228 0.01423 -0.0814 0.4827 1.0000
6.000 0.9550 0.02587 0.01556 -0.0734 0.2241 1.0000
6.250 0.9712 0.02930 0.01825 -0.0709 0.1507 1.0000
6.500 0.9960 0.03177 0.02051 -0.0697 0.1226 1.0000
6.750 1.0284 0.03456 0.02329 -0.0692 0.1090 1.0000
7.000 1.0612 0.03790 0.02676 -0.0689 0.1023 1.0000
7.250 1.0867 0.04077 0.02990 -0.0679 0.0948 1.0000
7.500 1.1094 0.04446 0.03390 -0.0668 0.0904 1.0000
7.750 1.1293 0.04839 0.03840 -0.0651 0.0902 1.0000
8.000 1.1458 0.05276 0.04326 -0.0633 0.0908 1.0000
8.250 1.1615 0.05782 0.04865 -0.0618 0.0919 1.0000
8.500 1.1557 0.06192 0.05395 -0.0577 0.0965 1.0000
8.750 1.1524 0.06736 0.05993 -0.0554 0.1003 1.0000
9.000 1.1585 0.07307 0.06590 -0.0541 0.1039 1.0000
9.250 1.1313 0.07833 0.07177 -0.0517 0.1091 1.0000
9.500 1.1090 0.08416 0.07788 -0.0508 0.1132 1.0000
9.750 1.1029 0.09001 0.08385 -0.0503 0.1195 1.0000
10.000 1.0615 0.09569 0.08967 -0.0515 0.1209 1.0000
10.250 1.0209 0.10441 0.09842 -0.0580 0.1236 1.0000
10.500 0.8776 0.10133 0.09551 -0.0442 0.1140 1.0000
10.750 0.9458 0.14315 0.13696 -0.0945 0.2804 1.0000
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Polar data table (+)
Polar graphs
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