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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(hs1620-il) HAM-STD HS1-620 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 20% at 34% chord Max camber 4.1% at 44% chord | Remove Airfoil details Airfoil plotter |
(kenmar-il) KENNEDY AND MARSDEN AIRFOIL | University of Alberta/Kennedy and Marsden high lift airfoil Max thickness 27.9% at 31% chord Max camber 7.7% at 36.9% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (hs1620-il,kenmar-il,hs1606-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hs1620-il | 50,000 | 9 | 16 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 50,000 | 5 | 25.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 100,000 | 9 | 43.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 100,000 | 5 | 38.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 200,000 | 9 | 59.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 200,000 | 5 | 51.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 500,000 | 9 | 72.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 500,000 | 5 | 57.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 1,000,000 | 9 | 76.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 1,000,000 | 5 | 70.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 50,000 | 9 | 3 at α=16° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 50,000 | 5 | 3.5 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 9 | 3 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 5 | 4.7 at α=-8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 9 | 5.1 at α=-7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 5 | 17.1 at α=-0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 9 | 28.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 5 | 59 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 9 | 70.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 5 | 97.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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