Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(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 | Remove Airfoil details Airfoil plotter |
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Polars for (dga1138-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dga1138-il | 50,000 | 9 | 38.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 50,000 | 5 | 37.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 100,000 | 9 | 54.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 100,000 | 5 | 49.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 200,000 | 9 | 69.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 200,000 | 5 | 57.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 500,000 | 9 | 79.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 500,000 | 5 | 67.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1138-il | 1,000,000 | 9 | 86.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1138-il | 1,000,000 | 5 | 77 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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