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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(raf32-il) RAF 32 AIRFOIL | RAF-32 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf32-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf32-il | 50,000 | 9 | 29.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 50,000 | 5 | 25.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 100,000 | 9 | 56.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 100,000 | 5 | 56.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 200,000 | 9 | 85.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 200,000 | 5 | 84.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 500,000 | 9 | 123.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 500,000 | 5 | 116.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 1,000,000 | 9 | 152.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 1,000,000 | 5 | 134.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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