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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(ht23-il) HT23 | Drela HT23 airfoil Max thickness 6.5% at 20.8% chord Max camber 1.1% at 22.6% 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 (ht23-il,hs1606-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ht23-il | 50,000 | 9 | 24.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 50,000 | 5 | 29 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 9 | 37.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 5 | 39.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 9 | 50.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 5 | 50.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 9 | 67.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 5 | 65.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 9 | 79.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 5 | 79.9 at α=7.25° | 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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