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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(hs1606-il) HAM-STD HS1-606 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 6% at 18% chord Max camber 4.4% at 46% chord | Remove Airfoil details Airfoil plotter |
(hq358-il) HQ 3.5/8 AIRFOIL | Quabeck HQ 3.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (hs1606-il,hq358-il,hq309-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hs1606-il | 50,000 | 9 | 45.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 50,000 | 5 | 45 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 100,000 | 9 | 68.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 100,000 | 5 | 66.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 200,000 | 9 | 95.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 200,000 | 5 | 90.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 500,000 | 9 | 133.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 500,000 | 5 | 121.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 1,000,000 | 9 | 160.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 1,000,000 | 5 | 108.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq358-il | 50,000 | 9 | 40.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq358-il | 50,000 | 5 | 43.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq358-il | 100,000 | 9 | 64.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq358-il | 100,000 | 5 | 63.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq358-il | 200,000 | 9 | 90.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq358-il | 200,000 | 5 | 84.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq358-il | 500,000 | 9 | 123.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq358-il | 500,000 | 5 | 106 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq358-il | 1,000,000 | 9 | 144.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq358-il | 1,000,000 | 5 | 109.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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