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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(raf30md-il) RAF 30 MOD AIRFOIL | RAF-30 MOD airfoil Max thickness 7.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf30md-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf30md-il | 50,000 | 9 | 26.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 50,000 | 5 | 25.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 100,000 | 9 | 35.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 100,000 | 5 | 31 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 200,000 | 9 | 42.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 200,000 | 5 | 36.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 500,000 | 9 | 47.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 500,000 | 5 | 52.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 1,000,000 | 9 | 59.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 1,000,000 | 5 | 65.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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