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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(hq1012-il) HQ 1.0/12 AIRFOIL | Quabeck HQ 1.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq1012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq1012-il | 50,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1012-il | 50,000 | 5 | 32 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1012-il | 100,000 | 9 | 47.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1012-il | 100,000 | 5 | 45.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1012-il | 200,000 | 9 | 63.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1012-il | 200,000 | 5 | 54.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1012-il | 500,000 | 9 | 75.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1012-il | 500,000 | 5 | 69.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1012-il | 1,000,000 | 9 | 87.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1012-il | 1,000,000 | 5 | 80.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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