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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(raf25-il) RAF 25 AIRFOIL | RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(rae104-il) RAE 104 AIRFOIL | RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(rae5214-il) RAE 5214 AIRFOIL | RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf25-il,rae104-il,rae5214-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf25-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 50,000 | 5 | 30.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 9 | 43.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 5 | 40.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 9 | 56.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 5 | 47.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 9 | 68.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 5 | 55.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 9 | 72.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 5 | 68.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 50,000 | 9 | 24.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 50,000 | 5 | 26.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 100,000 | 9 | 39.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 100,000 | 5 | 33.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 200,000 | 9 | 44.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 200,000 | 5 | 36.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 500,000 | 9 | 52.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 500,000 | 5 | 49.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae104-il | 1,000,000 | 9 | 58.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae104-il | 1,000,000 | 5 | 61.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 50,000 | 9 | 29.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 50,000 | 5 | 27.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 100,000 | 9 | 40.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 100,000 | 5 | 35.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 200,000 | 9 | 46.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 200,000 | 5 | 49.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 500,000 | 9 | 66.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 500,000 | 5 | 68.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5214-il | 1,000,000 | 9 | 83.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5214-il | 1,000,000 | 5 | 80.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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