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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(dga1182-il) D.G.A. 1182 | D.G.A. 1182 airfoil Max thickness 7.6% at 30% chord Max camber 0.9% at 20% chord | Remove Airfoil details Airfoil plotter |
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Polars for (dga1182-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dga1182-il | 50,000 | 9 | 22.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 50,000 | 5 | 20.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 100,000 | 9 | 24.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 100,000 | 5 | 27.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 200,000 | 9 | 29.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 200,000 | 5 | 37.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 500,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 500,000 | 5 | 47.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 1,000,000 | 9 | 57.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 1,000,000 | 5 | 55.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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