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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(ah88k130-il) AH 88-K-130/20 | Althaus AH 88-K-130/20 airfoil for use with flaps (K) Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah88k130-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah88k130-il | 50,000 | 9 | 23.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 50,000 | 5 | 23.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 100,000 | 9 | 42.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 100,000 | 5 | 43 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 200,000 | 9 | 80.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 200,000 | 5 | 79 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 500,000 | 9 | 121.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 500,000 | 5 | 113.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 1,000,000 | 9 | 147.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 1,000,000 | 5 | 136.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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