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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(glennmartin4-il) Glenn Martin 4 | Glenn Martin 4 airfoil Max thickness 15.5% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (glennmartin4-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| glennmartin4-il | 50,000 | 9 | 22 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 50,000 | 5 | 27.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 100,000 | 9 | 42.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 100,000 | 5 | 40.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 200,000 | 9 | 54.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 200,000 | 5 | 49.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 500,000 | 9 | 64.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 500,000 | 5 | 62.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 1,000,000 | 9 | 79.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 1,000,000 | 5 | 77.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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