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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(hq159-il) HQ 1.5/9 AIRFOIL | Quabeck HQ 1.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq159-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq159-il | 50,000 | 9 | 35.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159-il | 50,000 | 5 | 35.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159-il | 100,000 | 9 | 51.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159-il | 100,000 | 5 | 49.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159-il | 200,000 | 9 | 68.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159-il | 200,000 | 5 | 61.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159-il | 500,000 | 9 | 88.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159-il | 500,000 | 5 | 72.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159-il | 1,000,000 | 9 | 92.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159-il | 1,000,000 | 5 | 79.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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