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D.G.A. 1138 (dga1138-il)

D.G.A. 1138 - D.G.A. 1138 airfoil


Airfoil dga1138-il
Details Dat file Parser  
(dga1138-il) D.G.A. 1138
D.G.A. 1138 airfoil
Max thickness 6.9% at 30% chord.
Max camber 2.6% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
D.G.A. 1138
1.0000     0.0100
0.9500     0.0200
0.9000     0.0275
0.8000     0.0425
0.7000     0.0550
0.6000     0.0650
0.5000     0.0700
0.4000     0.0750
0.3000     0.0750
0.2000     0.0700
0.1500     0.0655
0.1000     0.0600
0.0750     0.0550
0.0500     0.0490
0.0250     0.0390
0.0125     0.0320
0.0000     0.0200
0.0125     0.0090
0.0250     0.0060
0.0500     0.0040
0.0750     0.0010
0.1000     0.0000
0.1500     0.0010
0.2000     0.0030
0.3000     0.0060
0.4000     0.0060
0.5000     0.0050
0.6000     0.0030
0.7000     0.0020
0.8000     0.0010
0.9000     0.0000
0.9500     0.0010
1.0000     0.0040
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Polars for D.G.A. 1138 (dga1138-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dga1138-il50,000938.1 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1138-il50,000537.4 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1138-il100,000954.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1138-il100,000549.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1138-il200,000969.3 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1138-il200,000557.4 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1138-il500,000979.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1138-il500,000567.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1138-il1,000,000986.6 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1138-il1,000,000577 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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