MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 50,000 Max Cl/Cd: 42.52 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409-il-50000-n5.txt Download as CSV file: xf-ma409-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4199 0.09650 0.08988 -0.0277 1.0000 0.0421
-8.750 -0.4240 0.09330 0.08679 -0.0281 1.0000 0.0411
-8.250 -0.4323 0.08463 0.07836 -0.0344 1.0000 0.0384
-8.000 -0.4294 0.08093 0.07471 -0.0357 1.0000 0.0382
-7.750 -0.4255 0.07697 0.07080 -0.0376 1.0000 0.0380
-7.500 -0.4201 0.07266 0.06653 -0.0401 1.0000 0.0378
-7.250 -0.4125 0.06791 0.06178 -0.0433 1.0000 0.0377
-7.000 -0.4018 0.06254 0.05637 -0.0473 1.0000 0.0376
-6.750 -0.3872 0.05645 0.05014 -0.0521 1.0000 0.0375
-6.500 -0.3677 0.04951 0.04290 -0.0578 1.0000 0.0379
-6.250 -0.3471 0.04507 0.03820 -0.0610 1.0000 0.0401
-6.000 -0.3239 0.04137 0.03415 -0.0635 1.0000 0.0439
-5.750 -0.2916 0.03507 0.02694 -0.0682 1.0000 0.0473
-5.500 -0.2633 0.03161 0.02289 -0.0698 1.0000 0.0519
-5.250 -0.2343 0.02909 0.01978 -0.0710 1.0000 0.0648
-5.000 -0.2055 0.02692 0.01717 -0.0717 1.0000 0.0845
-4.750 -0.1819 0.02685 0.01681 -0.0718 1.0000 0.1187
-4.500 -0.1560 0.02581 0.01545 -0.0718 1.0000 0.1340
-4.250 -0.1300 0.02479 0.01416 -0.0717 1.0000 0.1418
-4.000 -0.1038 0.02398 0.01299 -0.0716 1.0000 0.1507
-3.750 -0.0775 0.02324 0.01199 -0.0714 1.0000 0.1571
-3.500 -0.0508 0.02260 0.01109 -0.0712 1.0000 0.1639
-3.250 -0.0238 0.02213 0.01041 -0.0712 1.0000 0.1751
-3.000 0.0029 0.02171 0.00989 -0.0713 1.0000 0.1909
-2.750 0.0300 0.02130 0.00948 -0.0715 1.0000 0.2101
-2.500 0.0574 0.02090 0.00915 -0.0717 1.0000 0.2427
-2.250 0.0849 0.02053 0.00895 -0.0721 1.0000 0.3078
-2.000 0.1119 0.02014 0.00890 -0.0724 1.0000 0.4051
-1.750 0.1382 0.01964 0.00884 -0.0724 1.0000 0.5232
-1.500 0.1522 0.01856 0.00872 -0.0692 0.9956 1.0000
-1.250 0.1889 0.01888 0.00868 -0.0714 0.9893 1.0000
-1.000 0.2248 0.01922 0.00874 -0.0735 0.9832 1.0000
-0.750 0.2613 0.01957 0.00888 -0.0757 0.9776 1.0000
-0.500 0.2942 0.01988 0.00904 -0.0771 0.9703 1.0000
-0.250 0.3300 0.02019 0.00924 -0.0791 0.9623 1.0000
0.000 0.3693 0.02048 0.00947 -0.0817 0.9536 1.0000
0.250 0.4050 0.02069 0.00964 -0.0834 0.9416 1.0000
0.500 0.4418 0.02084 0.00980 -0.0852 0.9288 1.0000
0.750 0.4792 0.02092 0.00994 -0.0870 0.9147 1.0000
1.000 0.5133 0.02102 0.01012 -0.0882 0.9015 1.0000
1.250 0.5462 0.02114 0.01034 -0.0891 0.8888 1.0000
1.500 0.5793 0.02123 0.01060 -0.0900 0.8756 1.0000
1.750 0.6126 0.02127 0.01081 -0.0908 0.8614 1.0000
2.000 0.6454 0.02126 0.01099 -0.0914 0.8464 1.0000
2.250 0.6791 0.02116 0.01117 -0.0919 0.8303 1.0000
2.500 0.7110 0.02102 0.01127 -0.0918 0.8097 1.0000
2.750 0.7494 0.02062 0.01112 -0.0924 0.7879 1.0000
3.000 0.7873 0.02028 0.01105 -0.0926 0.7606 1.0000
3.250 0.8215 0.02020 0.01118 -0.0922 0.7288 1.0000
3.500 0.8422 0.02056 0.01184 -0.0904 0.6887 1.0000
3.750 0.8597 0.02022 0.01131 -0.0862 0.5928 1.0000
4.000 0.8842 0.02096 0.01160 -0.0840 0.5169 1.0000
4.250 0.8963 0.02193 0.01234 -0.0807 0.4056 1.0000
4.500 0.9022 0.02397 0.01308 -0.0772 0.2152 1.0000
4.750 0.9147 0.02696 0.01484 -0.0756 0.0658 1.0000
5.000 0.9341 0.02887 0.01661 -0.0743 0.0454 1.0000
5.250 0.9531 0.03053 0.01844 -0.0728 0.0395 1.0000
5.500 0.9707 0.03231 0.02044 -0.0711 0.0367 1.0000
5.750 0.9890 0.03407 0.02247 -0.0694 0.0338 1.0000
6.000 1.0058 0.03609 0.02460 -0.0678 0.0308 1.0000
6.250 1.0249 0.03828 0.02714 -0.0662 0.0291 1.0000
6.500 1.0480 0.04071 0.02990 -0.0649 0.0283 1.0000
6.750 1.0717 0.04357 0.03312 -0.0637 0.0277 1.0000
7.000 1.0927 0.04680 0.03679 -0.0624 0.0274 1.0000
7.250 1.1092 0.05030 0.04077 -0.0607 0.0271 1.0000
7.500 1.1205 0.05395 0.04492 -0.0588 0.0267 1.0000
7.750 1.1267 0.05771 0.04917 -0.0566 0.0262 1.0000
8.000 1.1280 0.06158 0.05349 -0.0542 0.0258 1.0000
8.250 1.1246 0.06552 0.05783 -0.0519 0.0256 1.0000
8.500 1.1167 0.06951 0.06218 -0.0496 0.0255 1.0000
8.750 1.1034 0.07336 0.06632 -0.0472 0.0256 1.0000
9.000 1.0870 0.07747 0.07068 -0.0455 0.0257 1.0000
9.250 1.0688 0.08206 0.07548 -0.0450 0.0259 1.0000
9.500 1.0497 0.08733 0.08093 -0.0461 0.0262 1.0000
9.750 1.0307 0.09342 0.08718 -0.0488 0.0266 1.0000
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Polar data table (+)
Polar graphs
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