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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(th25816-il) TH 25816 HALE AIRFOIL | Naval Air Development Center/Doug Hall high altitude Max thickness 25.7% at 48.3% chord Max camber 4% at 52.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (th25816-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| th25816-il | 50,000 | 9 | 2.4 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 50,000 | 5 | 7.1 at α=19° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 9 | 15.1 at α=17.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 5 | 12.2 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 9 | 21.5 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 5 | 19.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 9 | 54.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 5 | 47.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 9 | 74.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 5 | 59.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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