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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(lwk80080-il) LWK 80-080 | LWK 80-080 symmetrical airfoil Max thickness 8.1% at 40.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (lwk80080-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lwk80080-il | 50,000 | 9 | 22.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80080-il | 50,000 | 5 | 24.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80080-il | 100,000 | 9 | 37.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80080-il | 100,000 | 5 | 33.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80080-il | 200,000 | 9 | 45.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80080-il | 200,000 | 5 | 35.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80080-il | 500,000 | 9 | 47.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80080-il | 500,000 | 5 | 47.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80080-il | 1,000,000 | 9 | 54.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80080-il | 1,000,000 | 5 | 57.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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