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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(coanda3-il) Coanda 3 | Coanda 3 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (coanda3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| coanda3-il | 50,000 | 9 | 37.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 50,000 | 5 | 37.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 100,000 | 9 | 55.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 100,000 | 5 | 52.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 200,000 | 9 | 75.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 200,000 | 5 | 67.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 500,000 | 9 | 94.6 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 500,000 | 5 | 76 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 1,000,000 | 9 | 89 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 1,000,000 | 5 | 80.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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