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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(usa28-il) USA 28 AIRFOIL | USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa28-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa28-il | 50,000 | 9 | 21.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 50,000 | 5 | 31.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 100,000 | 9 | 54.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 100,000 | 5 | 54.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 200,000 | 9 | 75.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 200,000 | 5 | 72.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 500,000 | 9 | 97.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 500,000 | 5 | 87.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 1,000,000 | 9 | 114.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 1,000,000 | 5 | 88.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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