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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(raf32md-il) RAF 32 MOD AIRFOIL | RAF-32 MOD airfoil Max thickness 10.2% at 30% chord Max camber 4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf32md-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf32md-il | 50,000 | 9 | 38 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 50,000 | 5 | 37.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 9 | 62.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 5 | 61.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 9 | 87.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 5 | 83.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 9 | 120.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 5 | 110.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 5 | 124.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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