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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(cootie-il) WACO COOTIE AIRFOIL | Waco Cootie airfoil Max thickness 8.5% at 30% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(hs1404-il) HAM-STD HS1-404 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 4% at 18% chord Max camber 3.1% at 46% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cootie-il,hs1404-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cootie-il | 50,000 | 9 | 36.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 50,000 | 5 | 39.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 100,000 | 9 | 60.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 100,000 | 5 | 62.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 200,000 | 9 | 84 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 200,000 | 5 | 83.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 500,000 | 9 | 116 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 500,000 | 5 | 107.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cootie-il | 1,000,000 | 9 | 136.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cootie-il | 1,000,000 | 5 | 121.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 50,000 | 9 | 42.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 50,000 | 5 | 42.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 100,000 | 5 | 59.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 200,000 | 9 | 84.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 200,000 | 5 | 78.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 500,000 | 9 | 114.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 500,000 | 5 | 102.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1404-il | 1,000,000 | 9 | 134.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1404-il | 1,000,000 | 5 | 113.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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