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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(hq159b-il) HQ 1.5/9 B AIRFOIL | Quabeck HQ 1.5/9 B R/C sailplane airfoil Max thickness 9% at 37.1% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq159b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq159b-il | 50,000 | 9 | 35.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159b-il | 50,000 | 5 | 35.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159b-il | 100,000 | 9 | 51.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159b-il | 100,000 | 5 | 49.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159b-il | 200,000 | 9 | 67.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159b-il | 200,000 | 5 | 60.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159b-il | 500,000 | 9 | 84.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159b-il | 500,000 | 5 | 68 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq159b-il | 1,000,000 | 9 | 86.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq159b-il | 1,000,000 | 5 | 80.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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