MA409 (smoothed) (ma409sm-il)
MA409 (smoothed) - Michael Achterberg MA409 F1C class free flight airfoil (smoothed)
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(ma409sm-il) MA409 (smoothed) Michael Achterberg MA409 F1C class free flight airfoil (smoothed) Max thickness 6.7% at 23.8% chord. Max camber 3.3% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MA409 (smoothed)
1.00000 0.00034
0.99754 0.00094
0.99070 0.00259
0.98037 0.00498
0.96698 0.00793
0.95044 0.01136
0.93064 0.01521
0.90775 0.01937
0.88202 0.02373
0.85370 0.02817
0.82309 0.03261
0.79048 0.03694
0.75616 0.04112
0.72043 0.04505
0.68359 0.04869
0.64594 0.05198
0.60778 0.05486
0.56937 0.05732
0.53099 0.05933
0.49265 0.06089
0.45435 0.06202
0.41638 0.06270
0.37887 0.06291
0.34204 0.06260
0.30609 0.06172
0.27120 0.06025
0.23760 0.05819
0.20549 0.05555
0.17504 0.05234
0.14648 0.04859
0.11999 0.04433
0.09576 0.03961
0.07395 0.03450
0.05468 0.02913
0.03811 0.02369
0.02433 0.01831
0.01338 0.01305
0.00548 0.00797
0.00098 0.00318
0.00000 -0.00004
0.00098 -0.00302
0.00548 -0.00664
0.01338 -0.00968
0.02433 -0.01213
0.03811 -0.01400
0.05468 -0.01527
0.07395 -0.01590
0.09576 -0.01589
0.11999 -0.01527
0.14648 -0.01416
0.17504 -0.01264
0.20549 -0.01081
0.23760 -0.00875
0.27120 -0.00653
0.30609 -0.00421
0.34204 -0.00186
0.37887 0.00039
0.41638 0.00245
0.45435 0.00422
0.49265 0.00565
0.53099 0.00674
0.56937 0.00754
0.60778 0.00808
0.64594 0.00837
0.68359 0.00844
0.72043 0.00830
0.75616 0.00798
0.79048 0.00749
0.82309 0.00687
0.85370 0.00613
0.88202 0.00529
0.90775 0.00439
0.93064 0.00347
0.95044 0.00256
0.96698 0.00170
0.98037 0.00093
0.99070 0.00028
0.99754 -0.00018
1.00000 -0.00036
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Polars for MA409 (smoothed) (ma409sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ma409sm-il | 50,000 | 9 | 43.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 50,000 | 5 | 43.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 100,000 | 9 | 64.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 100,000 | 5 | 62.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 200,000 | 9 | 88.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 200,000 | 5 | 81.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 500,000 | 9 | 121.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 500,000 | 5 | 100.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 1,000,000 | 9 | 140.9 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 1,000,000 | 5 | 112.2 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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