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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(lwk80100-il) LWK 80-100 | LWK 80-100 symmetrical airfoil Max thickness 10.1% at 40.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (lwk80100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lwk80100-il | 50,000 | 9 | 26.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 50,000 | 5 | 26.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 100,000 | 9 | 59.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 100,000 | 5 | 31.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 200,000 | 9 | 44 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 200,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 500,000 | 9 | 49 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 500,000 | 5 | 51.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80100-il | 1,000,000 | 9 | 60.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80100-il | 1,000,000 | 5 | 61.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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