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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(supermarine371ii-il) Supermarine 371-II (tip) | Supermarine 371-II tip airfoil Max thickness 8.4% at 50% chord Max camber 0.9% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (supermarine371ii-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| supermarine371ii-il | 50,000 | 9 | 19.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 50,000 | 5 | 23.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 100,000 | 9 | 29.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 100,000 | 5 | 37.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 200,000 | 9 | 51.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 200,000 | 5 | 45.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 500,000 | 9 | 63.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 500,000 | 5 | 54.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 1,000,000 | 9 | 73.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 1,000,000 | 5 | 58.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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