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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(august160-il) AUGUST 160 | AUGUST 160 airfoil Max thickness 16% at 25% chord Max camber 5.4% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (august160-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| august160-il | 50,000 | 9 | 4.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 50,000 | 5 | 17.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 100,000 | 9 | 20.8 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 100,000 | 5 | 34.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 200,000 | 9 | 42.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 200,000 | 5 | 56.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 500,000 | 9 | 82.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 500,000 | 5 | 90.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 1,000,000 | 9 | 117.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 1,000,000 | 5 | 120.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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