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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(hq3518-il) HQ 3.5/18 AIRFOIL | Quabeck HQ 3.5/18 R/C sailplane airfoil Max thickness 18% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq3518-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq3518-il | 50,000 | 9 | 6.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 50,000 | 5 | 21.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 100,000 | 9 | 47.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 100,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 200,000 | 9 | 68.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 200,000 | 5 | 61.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 500,000 | 9 | 90.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 500,000 | 5 | 78.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 1,000,000 | 9 | 105.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 1,000,000 | 5 | 89.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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