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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(doa5-il) DORNIER A-5 AIRFOIL | Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord | Remove Airfoil details Airfoil plotter |
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Polars for (doa5-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| doa5-il | 50,000 | 9 | 29.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 50,000 | 5 | 25.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 100,000 | 9 | 41.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 100,000 | 5 | 35.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 200,000 | 9 | 52 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 200,000 | 5 | 49.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 500,000 | 9 | 75.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 500,000 | 5 | 59 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 1,000,000 | 9 | 87.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 1,000,000 | 5 | 68.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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