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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(hq308-il) HQ 3.0/8 AIRFOIL | Quabeck HQ 3.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx71089a-il) WORTMANN FX 71-089A AIRFOIL | Wortmann FX 71-089A airfoil Max thickness 8.9% at 22.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx63110-il) FX 63-110 AIRFOIL | Wortmann FX 63-110 airfoil Max thickness 11% at 30.8% chord Max camber 4.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(ah6407-il) AH-6-40-7 AIRFOIL | Althaus AH 6-407 airfoil Max thickness 6.9% at 20% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq308-il,fx71089a-il,fx63110-il,ah6407-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq308-il | 50,000 | 9 | 40.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 50,000 | 5 | 42.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 100,000 | 9 | 62.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 100,000 | 5 | 60.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 200,000 | 9 | 86.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 200,000 | 5 | 79.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 500,000 | 9 | 116.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 500,000 | 5 | 99.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 1,000,000 | 9 | 135.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 1,000,000 | 5 | 99.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 9 | 19.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 5 | 19.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 5 | 26.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 9 | 31.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 5 | 36.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 5 | 52.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 9 | 59.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 5 | 68 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 50,000 | 9 | 40 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 50,000 | 5 | 42.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 100,000 | 9 | 64.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 100,000 | 5 | 66.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 200,000 | 9 | 90.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 200,000 | 5 | 87.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 500,000 | 9 | 118.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 500,000 | 5 | 105.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63110-il | 1,000,000 | 9 | 136.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63110-il | 1,000,000 | 5 | 117.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 5 | 46.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 5 | 67.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 9 | 91.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 5 | 85.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 5 | 104 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 9 | 131.3 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 5 | 121.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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