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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(hq2511-il) HQ 2.5/11 AIRFOIL | Quabeck HQ 2.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq2511-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2511-il | 50,000 | 9 | 35.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 50,000 | 5 | 37.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 100,000 | 9 | 56.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 100,000 | 5 | 54.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 200,000 | 9 | 78.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 200,000 | 5 | 70.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 500,000 | 9 | 102.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 500,000 | 5 | 84.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 1,000,000 | 9 | 107.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 1,000,000 | 5 | 92.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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