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 |
(hq3011-il) HQ 3.0/11 AIRFOIL | Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3514-il) HQ 3.5/14 AIRFOIL | Quabeck HQ 3.5/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq3015-il,hq3011-il,hq3514-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 | |
| hq3011-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 50,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 100,000 | 9 | 58.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 100,000 | 5 | 57.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 200,000 | 9 | 81.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 200,000 | 5 | 75.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 500,000 | 9 | 111.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 500,000 | 5 | 92.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 1,000,000 | 9 | 124.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 1,000,000 | 5 | 101.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 50,000 | 9 | 29.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 50,000 | 5 | 33.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 100,000 | 9 | 55.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 100,000 | 5 | 54.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 200,000 | 9 | 80 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 200,000 | 5 | 71.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 500,000 | 9 | 100.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 500,000 | 5 | 86.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 1,000,000 | 9 | 112.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 1,000,000 | 5 | 99.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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