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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(lwk80120k25-il) LWK 80-120/K25 | LWK 80-120/K25 symmetrical airfoil Max thickness 12.1% at 40.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (lwk80120k25-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lwk80120k25-il | 50,000 | 9 | 27.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80120k25-il | 50,000 | 5 | 27.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80120k25-il | 100,000 | 9 | 40.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80120k25-il | 100,000 | 5 | 30.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80120k25-il | 200,000 | 9 | 41.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80120k25-il | 200,000 | 5 | 38 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80120k25-il | 500,000 | 9 | 51.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80120k25-il | 500,000 | 5 | 51.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk80120k25-il | 1,000,000 | 9 | 62.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk80120k25-il | 1,000,000 | 5 | 63.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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