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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(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 |
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Polars for (hq2195-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
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