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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(hq3015-il) HQ 3.0/15 AIRFOIL | Quabeck HQ 3.0/15 R/C sailplane airfoil Max thickness 15% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq3015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq3015-il | 50,000 | 9 | 25.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 50,000 | 5 | 30.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 100,000 | 9 | 52.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 100,000 | 5 | 51.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 200,000 | 9 | 75.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 200,000 | 5 | 67.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 500,000 | 9 | 97.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 500,000 | 5 | 84 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 1,000,000 | 9 | 111.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 1,000,000 | 5 | 95.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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