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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(glennmartin3-il) Glenn Martin 3 | Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (glennmartin3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| glennmartin3-il | 50,000 | 9 | 32.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 5 | 29.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 9 | 41.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 5 | 38.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 9 | 54.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 5 | 47.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 9 | 62.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 9 | 78.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 5 | 78.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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