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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(hq07-il) HQ 0/7 AIRFOIL | Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq07-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq07-il | 50,000 | 9 | 26.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 50,000 | 5 | 24.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 100,000 | 9 | 35.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 100,000 | 5 | 31.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 200,000 | 9 | 43.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 200,000 | 5 | 36.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 500,000 | 9 | 50.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 500,000 | 5 | 46.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 1,000,000 | 9 | 59.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 1,000,000 | 5 | 56.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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