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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(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL | Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hh02-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hh02-il | 50,000 | 9 | 30.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 50,000 | 5 | 33.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 100,000 | 9 | 46.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 100,000 | 5 | 45.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 200,000 | 9 | 60.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 200,000 | 5 | 56.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 500,000 | 9 | 76.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 500,000 | 5 | 72.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 1,000,000 | 9 | 89.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 1,000,000 | 5 | 84.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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