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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(coanda2-il) Coanda 2 | Coanda 2 airfoil Max thickness 6% at 30% chord Max camber 2.9% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (coanda2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| coanda2-il | 50,000 | 9 | 37.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 50,000 | 5 | 37.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 100,000 | 5 | 48 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 200,000 | 9 | 64.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 200,000 | 5 | 49.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 500,000 | 9 | 62.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 500,000 | 5 | 52.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 1,000,000 | 9 | 58.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 1,000,000 | 5 | 58.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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