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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(ag38-il) AG38 | Drela AG38 airfoil Max thickness 7% at 27.7% chord Max camber 2% at 36.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag38-il | 50,000 | 9 | 34.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 50,000 | 5 | 36 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 100,000 | 9 | 49.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 100,000 | 5 | 48.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 200,000 | 9 | 64 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 200,000 | 5 | 59.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 500,000 | 9 | 81.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 500,000 | 5 | 73.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag38-il | 1,000,000 | 9 | 92 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag38-il | 1,000,000 | 5 | 85.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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