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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(ah63k127-il) AH 63-K-127/24 | Althaus AH 63-K-127/24 airfoil for use with flaps (K) Max thickness 12.7% at 40.2% chord Max camber 3.8% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah63k127-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah63k127-il | 50,000 | 9 | 25.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 50,000 | 5 | 23 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 100,000 | 9 | 43.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 100,000 | 5 | 44.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 200,000 | 9 | 83.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 200,000 | 5 | 81.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 500,000 | 9 | 127.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 500,000 | 5 | 115.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah63k127-il | 1,000,000 | 9 | 152.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah63k127-il | 1,000,000 | 5 | 137.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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