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MA409 (smoothed) (ma409sm-il)

MA409 (smoothed) - Michael Achterberg MA409 F1C class free flight airfoil (smoothed)


Airfoil ma409sm-il
Details Dat file Parser  
(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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ma409sm-il50,000943.5 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409sm-il50,000543.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409sm-il100,000964.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409sm-il100,000562.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409sm-il200,000988.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409sm-il200,000581.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409sm-il500,0009121.6 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409sm-il500,0005100.9 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409sm-il1,000,0009140.9 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409sm-il1,000,0005112.2 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
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