MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 100,000 Max Cl/Cd: 64.23 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409sm-il-100000.txt Download as CSV file: xf-ma409sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4176 0.09826 0.09331 -0.0247 1.0000 0.0888
-7.750 -0.4335 0.09740 0.09260 -0.0263 1.0000 0.0904
-7.500 -0.4428 0.09575 0.09106 -0.0344 1.0000 0.0912
-7.250 -0.4298 0.09011 0.08542 -0.0260 1.0000 0.0933
-7.000 -0.4227 0.08710 0.08243 -0.0241 1.0000 0.0962
-6.750 -0.4210 0.08436 0.07975 -0.0247 1.0000 0.0997
-6.500 -0.4206 0.08137 0.07676 -0.0421 1.0000 0.1048
-6.250 -0.4174 0.07730 0.07279 -0.0334 1.0000 0.1063
-6.000 -0.4109 0.07453 0.07005 -0.0300 1.0000 0.1091
-5.750 -0.3983 0.07097 0.06644 -0.0373 1.0000 0.1173
-5.500 -0.3893 0.06661 0.06209 -0.0390 1.0000 0.1202
-5.250 -0.3664 0.06305 0.05829 -0.0471 1.0000 0.1320
-5.000 -0.3589 0.05910 0.05445 -0.0444 1.0000 0.1338
-4.750 -0.3477 0.05634 0.05172 -0.0424 1.0000 0.1373
-4.500 -0.2847 0.03937 0.03366 -0.0621 1.0000 0.0751
-4.250 -0.2506 0.03294 0.02658 -0.0665 1.0000 0.0697
-4.000 -0.2159 0.02837 0.02124 -0.0693 1.0000 0.0696
-3.750 -0.1794 0.02445 0.01647 -0.0713 1.0000 0.0689
-3.500 -0.1471 0.02219 0.01372 -0.0722 1.0000 0.0729
-3.250 -0.1165 0.02070 0.01194 -0.0728 1.0000 0.0840
-3.000 -0.0848 0.01921 0.01025 -0.0734 1.0000 0.0973
-2.750 -0.0552 0.01828 0.00926 -0.0738 1.0000 0.1222
-2.500 -0.0257 0.01747 0.00843 -0.0742 1.0000 0.1585
-2.250 0.0032 0.01677 0.00791 -0.0747 1.0000 0.2052
-2.000 0.0308 0.01638 0.00762 -0.0750 1.0000 0.2575
-1.750 0.0576 0.01602 0.00748 -0.0751 1.0000 0.3093
-1.500 0.0849 0.01572 0.00736 -0.0754 1.0000 0.3697
-1.250 0.1126 0.01531 0.00724 -0.0756 1.0000 0.4453
-1.000 0.1427 0.01460 0.00713 -0.0762 1.0000 0.5859
-0.750 0.1501 0.01372 0.00704 -0.0716 1.0000 1.0000
-0.500 0.1757 0.01403 0.00708 -0.0717 1.0000 1.0000
-0.250 0.2004 0.01437 0.00723 -0.0718 1.0000 1.0000
0.000 0.2246 0.01475 0.00745 -0.0717 1.0000 1.0000
0.250 0.2482 0.01518 0.00776 -0.0717 1.0000 1.0000
0.500 0.2714 0.01565 0.00814 -0.0717 1.0000 1.0000
0.750 0.3006 0.01617 0.00859 -0.0730 0.9973 1.0000
1.000 0.3494 0.01665 0.00901 -0.0778 0.9868 1.0000
1.250 0.3968 0.01705 0.00938 -0.0822 0.9754 1.0000
1.500 0.4431 0.01736 0.00969 -0.0863 0.9634 1.0000
1.750 0.4885 0.01755 0.00992 -0.0900 0.9506 1.0000
2.000 0.5328 0.01762 0.01005 -0.0932 0.9370 1.0000
2.250 0.5764 0.01757 0.01009 -0.0960 0.9229 1.0000
2.500 0.6196 0.01738 0.01005 -0.0986 0.9084 1.0000
2.750 0.6633 0.01704 0.00984 -0.1008 0.8938 1.0000
3.000 0.7053 0.01656 0.00952 -0.1025 0.8787 1.0000
3.250 0.7455 0.01598 0.00915 -0.1035 0.8628 1.0000
3.500 0.7786 0.01553 0.00887 -0.1031 0.8416 1.0000
3.750 0.8151 0.01496 0.00845 -0.1031 0.8205 1.0000
4.000 0.8458 0.01461 0.00823 -0.1021 0.7924 1.0000
4.250 0.8734 0.01442 0.00814 -0.1007 0.7571 1.0000
4.500 0.8981 0.01416 0.00786 -0.0980 0.7001 1.0000
4.750 0.9179 0.01429 0.00769 -0.0947 0.6201 1.0000
5.000 0.9366 0.01482 0.00790 -0.0919 0.5403 1.0000
5.250 0.9513 0.01572 0.00830 -0.0888 0.4342 1.0000
5.500 0.9490 0.01894 0.00953 -0.0838 0.1413 1.0000
5.750 0.9608 0.02144 0.01147 -0.0809 0.0848 1.0000
6.000 0.9772 0.02320 0.01326 -0.0786 0.0723 1.0000
6.250 0.9954 0.02502 0.01503 -0.0769 0.0630 1.0000
6.500 1.0177 0.02682 0.01682 -0.0756 0.0573 1.0000
6.750 1.0448 0.03016 0.02004 -0.0752 0.0540 1.0000
7.000 1.0722 0.03250 0.02266 -0.0742 0.0529 1.0000
7.250 1.0980 0.03539 0.02592 -0.0731 0.0524 1.0000
7.500 1.1190 0.03787 0.02889 -0.0713 0.0503 1.0000
7.750 1.1375 0.04087 0.03237 -0.0694 0.0488 1.0000
8.000 1.1532 0.04496 0.03704 -0.0672 0.0502 1.0000
8.250 1.1656 0.04972 0.04223 -0.0650 0.0522 1.0000
8.500 1.1711 0.05495 0.04841 -0.0609 0.0604 1.0000
11.000 0.8373 0.12592 0.12184 -0.0582 0.1578 1.0000
11.250 0.7868 0.13142 0.12723 -0.0652 0.1509 1.0000
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Polar data table (+)
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