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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(hq309-il) HQ 3.0/9 AIRFOIL | Quabeck HQ 3.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca000834-il) NACA 0008-34 | NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq309-il,naca000834-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq309-il | 50,000 | 9 | 39.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 50,000 | 5 | 41.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 100,000 | 9 | 61.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 100,000 | 5 | 59.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 200,000 | 9 | 84.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 200,000 | 5 | 78.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 500,000 | 9 | 114.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 500,000 | 5 | 96.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 1,000,000 | 9 | 132.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 1,000,000 | 5 | 101.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 50,000 | 9 | 18.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 50,000 | 5 | 18.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 100,000 | 9 | 24.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 100,000 | 5 | 30.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 200,000 | 9 | 40.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 200,000 | 5 | 36 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 500,000 | 9 | 57.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 500,000 | 5 | 37.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 1,000,000 | 9 | 43 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 1,000,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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