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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(hq1511-il) HQ 1.5/11 AIRFOIL | Quabeck HQ 1.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq1511-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq1511-il | 50,000 | 9 | 33.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 50,000 | 5 | 34.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 100,000 | 9 | 50.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 200,000 | 9 | 67.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 200,000 | 5 | 59.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 500,000 | 9 | 82.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 500,000 | 5 | 74 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 1,000,000 | 9 | 94.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 1,000,000 | 5 | 82.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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