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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(usa40b-il) USA 40 B AIRFOIL | USA-40B airfoil Max thickness 13.6% at 20% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa40b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa40b-il | 50,000 | 9 | 25.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 50,000 | 5 | 31.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 100,000 | 9 | 39.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 100,000 | 5 | 45.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 200,000 | 9 | 56.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 200,000 | 5 | 62 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 500,000 | 9 | 85.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 500,000 | 5 | 88.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40b-il | 1,000,000 | 9 | 111.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40b-il | 1,000,000 | 5 | 112 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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