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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(raf15-il) RAF 15 AIRFOIL | RAF-15 airfoil Max thickness 6.5% at 15% chord Max camber 2.6% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf15-il | 50,000 | 9 | 32.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 50,000 | 5 | 33.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 100,000 | 9 | 43.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 100,000 | 5 | 47.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 200,000 | 9 | 59.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 200,000 | 5 | 59.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 500,000 | 9 | 78.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 500,000 | 5 | 76.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 1,000,000 | 9 | 92.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 1,000,000 | 5 | 89.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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