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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(hq2510-il) HQ 2.5/10 AIRFOIL | Quabeck HQ 2.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq2510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2510-il | 50,000 | 9 | 37 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 50,000 | 5 | 38.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 100,000 | 9 | 57.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 100,000 | 5 | 55.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 200,000 | 9 | 79.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 200,000 | 5 | 72.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 500,000 | 9 | 105.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 500,000 | 5 | 85.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 1,000,000 | 9 | 113.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 1,000,000 | 5 | 92.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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