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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(e297-il) EPPLER 297 AIRFOIL | Eppler E297 tailplane airfoil Max thickness 11.4% at 37.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e297-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e297-il | 50,000 | 9 | 29.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e297-il | 50,000 | 5 | 28.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e297-il | 100,000 | 9 | 43.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e297-il | 100,000 | 5 | 34.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e297-il | 200,000 | 9 | 46.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e297-il | 200,000 | 5 | 39.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e297-il | 500,000 | 9 | 56 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e297-il | 500,000 | 5 | 51.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e297-il | 1,000,000 | 9 | 61.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e297-il | 1,000,000 | 5 | 60.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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