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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(ah83150q-il) AH 83-150 Q | Althaus AH 83-150 Q airfoil Max thickness 15% at 40.2% chord Max camber 4.1% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah83150q-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah83150q-il | 50,000 | 9 | 6.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 50,000 | 5 | 15.9 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 100,000 | 9 | 39.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 100,000 | 5 | 35.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 200,000 | 9 | 73.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 200,000 | 5 | 71.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 500,000 | 9 | 109.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 500,000 | 5 | 102.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 1,000,000 | 9 | 134.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 1,000,000 | 5 | 122.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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