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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(raf27-il) RAF 27 AIRFOIL | RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf27-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf27-il | 50,000 | 9 | 28.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 50,000 | 5 | 27.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 100,000 | 9 | 39.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 100,000 | 5 | 36.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 200,000 | 9 | 49.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 200,000 | 5 | 43.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 500,000 | 9 | 56.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 500,000 | 5 | 58.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 1,000,000 | 9 | 69.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 1,000,000 | 5 | 71.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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