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MA409 (original) (modified line 7) (ma409-il)

MA409 (original) (modified line 7) - Michael Achterberg MA409 F1C class free flight airfoil (original)


Airfoil ma409-il
Details Dat file Parser  
(ma409-il) MA409 (original) (modified line 7)
Michael Achterberg MA409 F1C class free flight airfoil (original)
Max thickness 6.8% at 25% chord.
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MA409 (original) (modified line 7)
   1.00000   0.00070
   0.95000   0.01246
   0.90000   0.02308
   0.80000   0.04015
   0.70000   0.05236
   0.60000   0.06154
   0.55000   0.06543
   0.50000   0.06945
   0.45000   0.07186
   0.40000   0.07391
   0.35000   0.07434
   0.30000   0.07398
   0.25000   0.07302
   0.20000   0.06925
   0.15000   0.06421
   0.10000   0.05673
   0.07500   0.05132
   0.05000   0.04479
   0.02500   0.03500
   0.01250   0.02831
   0.00000   0.01749
   0.01250   0.00878
   0.02500   0.00437
   0.05000   0.00082
   0.07500   0.00022
   0.10000   0.00000
   0.15000   0.00122
   0.20000   0.00280
   0.25000   0.00514
   0.30000   0.00789
   0.35000   0.01031
   0.40000   0.01229
   0.45000   0.01424
   0.50000   0.01499
   0.55000   0.01525
   0.60000   0.01536
   0.70000   0.01384
   0.80000   0.01107
   0.90000   0.00704
   0.95000   0.00355
   1.00000   0.00000
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Polars for MA409 (original) (modified line 7) (ma409-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ma409-il50,000942.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409-il50,000542.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409-il100,000961.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409-il100,000559.6 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409-il200,000981.5 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409-il200,000572.8 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409-il500,000999.3 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409-il500,000589.3 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ma409-il1,000,0009110.6 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ma409-il1,000,000594.8 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
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