Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(hs1708-il) HAM-STD HS1-708 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 7.9% at 22% chord Max camber 5% at 46% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (hs1708-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hs1708-il | 50,000 | 9 | 42.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 50,000 | 5 | 43 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 100,000 | 9 | 67.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 100,000 | 5 | 66.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 200,000 | 9 | 97.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 200,000 | 5 | 92.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 500,000 | 9 | 139.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 500,000 | 5 | 120.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 1,000,000 | 9 | 169 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 1,000,000 | 5 | 117 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||