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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(marske2-il) MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYBRID) | Marske Pioneer IA airfoil (NACA 23112/43012A hybrid) Max thickness 12.1% at 25% chord Max camber 2.7% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (marske2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| marske2-il | 50,000 | 9 | 18.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske2-il | 50,000 | 5 | 24 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske2-il | 100,000 | 9 | 28.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske2-il | 100,000 | 5 | 35.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske2-il | 200,000 | 9 | 43 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske2-il | 200,000 | 5 | 51.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske2-il | 500,000 | 9 | 72.4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske2-il | 500,000 | 5 | 77.5 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske2-il | 1,000,000 | 9 | 99 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske2-il | 1,000,000 | 5 | 97 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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