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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(arad6-il) ARA-D 6% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord Max camber 5% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (arad6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| arad6-il | 50,000 | 9 | 46 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 50,000 | 5 | 45.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 100,000 | 9 | 68.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 100,000 | 5 | 66.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 200,000 | 9 | 93 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 200,000 | 5 | 86 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 500,000 | 9 | 122.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 500,000 | 5 | 105.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 1,000,000 | 9 | 139.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 1,000,000 | 5 | 106 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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