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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(glennmartin2-il) Glenn Martin 2 | Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (glennmartin2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| glennmartin2-il | 50,000 | 9 | 24.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 50,000 | 5 | 31.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 100,000 | 9 | 46.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 100,000 | 5 | 45.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 200,000 | 9 | 58.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 200,000 | 5 | 57.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 500,000 | 9 | 78.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 500,000 | 5 | 78.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 1,000,000 | 9 | 102.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 1,000,000 | 5 | 101.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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