MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 50,000 Max Cl/Cd: 43.56 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409sm-il-50000-n5.txt Download as CSV file: xf-ma409sm-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4311 0.09395 0.08696 -0.0285 1.0000 0.0504
-7.500 -0.4290 0.09062 0.08369 -0.0290 1.0000 0.0497
-7.250 -0.4273 0.08716 0.08032 -0.0304 1.0000 0.0494
-7.000 -0.4248 0.08351 0.07673 -0.0323 1.0000 0.0493
-6.750 -0.4208 0.07959 0.07287 -0.0348 1.0000 0.0495
-6.500 -0.4149 0.07539 0.06869 -0.0378 1.0000 0.0496
-6.250 -0.4067 0.07084 0.06415 -0.0413 1.0000 0.0497
-6.000 -0.3957 0.06598 0.05925 -0.0451 1.0000 0.0498
-5.750 -0.3817 0.06081 0.05399 -0.0490 1.0000 0.0496
-5.500 -0.3646 0.05537 0.04838 -0.0531 1.0000 0.0491
-5.250 -0.3434 0.04954 0.04227 -0.0577 1.0000 0.0487
-5.000 -0.3179 0.04370 0.03596 -0.0623 1.0000 0.0488
-4.750 -0.2891 0.03826 0.02986 -0.0662 1.0000 0.0494
-4.500 -0.2578 0.03358 0.02430 -0.0691 1.0000 0.0512
-4.250 -0.2333 0.03161 0.02217 -0.0698 1.0000 0.0566
-4.000 -0.2037 0.02897 0.01889 -0.0709 1.0000 0.0624
-3.750 -0.1745 0.02661 0.01602 -0.0714 1.0000 0.0670
-3.500 -0.1469 0.02520 0.01427 -0.0716 1.0000 0.0785
-3.250 -0.1197 0.02389 0.01272 -0.0716 1.0000 0.0908
-3.000 -0.0928 0.02288 0.01169 -0.0717 1.0000 0.1094
-2.750 -0.0650 0.02196 0.01064 -0.0718 1.0000 0.1352
-2.250 -0.0098 0.02078 0.00940 -0.0723 1.0000 0.2175
-2.000 0.0174 0.02035 0.00904 -0.0725 1.0000 0.2647
-1.750 0.0443 0.01997 0.00875 -0.0726 1.0000 0.3166
-1.500 0.0712 0.01961 0.00853 -0.0727 1.0000 0.3756
-1.250 0.0978 0.01921 0.00830 -0.0728 1.0000 0.4479
-1.000 0.1233 0.01861 0.00815 -0.0724 1.0000 0.5569
-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 0.2300 0.01886 0.00828 -0.0680 0.9981 1.0000
0.500 0.2718 0.01929 0.00855 -0.0714 0.9880 1.0000
0.750 0.3129 0.01970 0.00884 -0.0745 0.9776 1.0000
1.000 0.3537 0.02008 0.00913 -0.0776 0.9668 1.0000
1.250 0.3943 0.02040 0.00941 -0.0805 0.9555 1.0000
1.500 0.4336 0.02067 0.00968 -0.0830 0.9432 1.0000
1.750 0.4711 0.02089 0.00995 -0.0850 0.9300 1.0000
2.000 0.5084 0.02106 0.01017 -0.0870 0.9162 1.0000
2.250 0.5442 0.02118 0.01038 -0.0884 0.9013 1.0000
2.500 0.5788 0.02126 0.01062 -0.0895 0.8852 1.0000
2.750 0.6143 0.02128 0.01078 -0.0906 0.8688 1.0000
3.000 0.6496 0.02121 0.01087 -0.0915 0.8518 1.0000
3.250 0.6855 0.02106 0.01090 -0.0922 0.8345 1.0000
3.500 0.7154 0.02101 0.01110 -0.0918 0.8124 1.0000
3.750 0.7487 0.02084 0.01114 -0.0918 0.7908 1.0000
4.000 0.7807 0.02070 0.01120 -0.0914 0.7659 1.0000
4.250 0.8115 0.02059 0.01130 -0.0907 0.7377 1.0000
4.500 0.8400 0.02061 0.01151 -0.0897 0.7048 1.0000
4.750 0.8697 0.02062 0.01176 -0.0887 0.6691 1.0000
5.000 0.8967 0.02078 0.01206 -0.0873 0.6274 1.0000
5.250 0.9169 0.02105 0.01214 -0.0842 0.5529 1.0000
5.500 0.9282 0.02193 0.01228 -0.0800 0.4322 1.0000
5.750 0.9397 0.02328 0.01303 -0.0770 0.3114 1.0000
6.000 0.9484 0.02572 0.01441 -0.0745 0.1540 1.0000
6.250 0.9618 0.02839 0.01648 -0.0728 0.0895 1.0000
6.500 0.9788 0.03038 0.01848 -0.0711 0.0725 1.0000
6.750 0.9960 0.03221 0.02039 -0.0695 0.0608 1.0000
7.000 1.0130 0.03420 0.02243 -0.0678 0.0547 1.0000
7.250 1.0349 0.03626 0.02474 -0.0663 0.0510 1.0000
7.500 1.0582 0.03840 0.02713 -0.0651 0.0466 1.0000
7.750 1.0785 0.04104 0.02976 -0.0643 0.0420 1.0000
8.000 1.1016 0.04363 0.03281 -0.0631 0.0396 1.0000
8.250 1.1224 0.04681 0.03656 -0.0618 0.0383 1.0000
8.500 1.1386 0.05029 0.04054 -0.0601 0.0374 1.0000
8.750 1.1499 0.05402 0.04478 -0.0581 0.0367 1.0000
9.000 1.1562 0.05793 0.04918 -0.0559 0.0364 1.0000
9.250 1.1574 0.06197 0.05370 -0.0535 0.0361 1.0000
9.500 1.1539 0.06601 0.05815 -0.0511 0.0358 1.0000
9.750 1.1458 0.07002 0.06252 -0.0488 0.0355 1.0000
10.000 1.1325 0.07393 0.06672 -0.0464 0.0353 1.0000
10.250 1.1150 0.07800 0.07104 -0.0445 0.0353 1.0000
10.500 1.0948 0.08264 0.07590 -0.0438 0.0356 1.0000
10.750 1.0730 0.08807 0.08153 -0.0448 0.0360 1.0000
11.000 1.0508 0.09450 0.08811 -0.0477 0.0367 1.0000
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Polar data table (+)
Polar graphs
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