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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(hq258-il) HQ 2.5/8 AIRFOIL | Quabeck HQ 2.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(e715-il) EPPLER 715 AIRFOIL | Eppler E715 tailplane airfoil Max thickness 15% at 33.1% chord Max camber 2.8% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq258-il,e715-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq258-il | 50,000 | 9 | 39.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq258-il | 50,000 | 5 | 40.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq258-il | 100,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq258-il | 100,000 | 5 | 57.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq258-il | 200,000 | 9 | 80.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq258-il | 200,000 | 5 | 74 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq258-il | 500,000 | 9 | 108.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq258-il | 500,000 | 5 | 90.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq258-il | 1,000,000 | 9 | 124.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq258-il | 1,000,000 | 5 | 96.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 50,000 | 9 | 5.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 50,000 | 5 | 15.7 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 100,000 | 9 | 43.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 100,000 | 5 | 44.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 200,000 | 9 | 74.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 200,000 | 5 | 74.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 500,000 | 9 | 113.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 500,000 | 5 | 98 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 1,000,000 | 9 | 136.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 1,000,000 | 5 | 111.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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