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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(supermarine371i-il) Supermarine 371-I (root) | Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (supermarine371i-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
supermarine371i-il | 50,000 | 9 | 28.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
supermarine371i-il | 50,000 | 5 | 27.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
supermarine371i-il | 100,000 | 9 | 46.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
supermarine371i-il | 100,000 | 5 | 41 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
supermarine371i-il | 200,000 | 9 | 57.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
supermarine371i-il | 200,000 | 5 | 52.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
supermarine371i-il | 500,000 | 9 | 78.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
supermarine371i-il | 500,000 | 5 | 64 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
supermarine371i-il | 1,000,000 | 9 | 89.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
supermarine371i-il | 1,000,000 | 5 | 66.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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