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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(hq2090sm-il) HQ-2.0/9 9.0% smoothed | Quabeck HQ 2.0/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq2512-il) HQ 2.5/12 AIRFOIL | Quabeck HQ 2.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3010-il) HQ 3.0/10 AIRFOIL | Quabeck HQ 3.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq2195-il) HQ 2.1/9.5 AIRFOIL | Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord | Remove Airfoil details Airfoil plotter |
(hq259b-il) HQ 2.5/9 B AIRFOIL | Quabeck HQ 2.5/9 B R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 55% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq2090sm-il,hq2512-il,hq3010-il,hq2195-il,hq259b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2090sm-il | 50,000 | 9 | 36.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 50,000 | 5 | 37.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 100,000 | 9 | 55.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 100,000 | 5 | 53.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 200,000 | 9 | 73.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 200,000 | 5 | 68.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 500,000 | 9 | 97.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 500,000 | 5 | 79.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 1,000,000 | 9 | 104.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 1,000,000 | 5 | 87.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 50,000 | 9 | 33.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 50,000 | 5 | 36.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 100,000 | 9 | 55.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 100,000 | 5 | 53.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 200,000 | 9 | 76.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 200,000 | 5 | 70.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 500,000 | 9 | 100.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 500,000 | 5 | 83.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 1,000,000 | 9 | 108.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 1,000,000 | 5 | 92.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3010-il | 50,000 | 9 | 37.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3010-il | 50,000 | 5 | 39.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3010-il | 100,000 | 9 | 60 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3010-il | 100,000 | 5 | 58.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3010-il | 200,000 | 9 | 83.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3010-il | 200,000 | 5 | 77.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3010-il | 500,000 | 9 | 113.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3010-il | 500,000 | 5 | 92.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3010-il | 1,000,000 | 9 | 126 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3010-il | 1,000,000 | 5 | 99.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 50,000 | 9 | 37.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 50,000 | 5 | 37.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 5 | 52.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 9 | 74.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 5 | 79 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 9 | 101 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 50,000 | 9 | 39 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 50,000 | 5 | 39.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 100,000 | 9 | 58.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 100,000 | 5 | 56.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 200,000 | 9 | 79.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 200,000 | 5 | 73.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 500,000 | 9 | 105.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 500,000 | 5 | 84.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 1,000,000 | 9 | 112.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 1,000,000 | 5 | 91.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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