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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(ah93157-il) AH 93-157 | Althaus AH 93-157 airfoil Max thickness 15.7% at 39.6% chord Max camber 3.5% at 41.7% chord | Remove Airfoil details Airfoil plotter |
(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL | Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord | Remove Airfoil details Airfoil plotter |
(n64008a-il) NACA 64-008A AIRFOIL | NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah93157-il,sc1012r8-il,n64008a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93157-il | 50,000 | 9 | 4.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 50,000 | 5 | 14.4 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 100,000 | 9 | 40 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 100,000 | 5 | 37.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 200,000 | 9 | 74.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 200,000 | 5 | 66.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 500,000 | 9 | 100.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 500,000 | 5 | 92 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 1,000,000 | 9 | 120.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 1,000,000 | 5 | 112.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 9 | 23.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 9 | 34 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 5 | 37.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 9 | 46.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 5 | 50.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 5 | 72.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 9 | 88.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 5 | 90.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 9 | 19.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 5 | 23.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 9 | 32.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 5 | 30.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 9 | 41 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 5 | 35 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 9 | 46.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 5 | 44.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 9 | 49.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 5 | 59.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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