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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(hq208-il) HQ 2.0/8 AIRFOIL | Quabeck HQ 2.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq208-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq208-il | 50,000 | 9 | 37.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 50,000 | 5 | 38.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 100,000 | 9 | 55.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 100,000 | 5 | 53.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 200,000 | 9 | 74.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 200,000 | 5 | 68.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 500,000 | 9 | 98.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 500,000 | 5 | 83.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 1,000,000 | 9 | 112.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 1,000,000 | 5 | 84.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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