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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(mh114-il) MH 114 13.02% | Martin Hepperle MH 114 for a propeller for ultralight Max thickness 13% at 28.1% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(sc20606-il) NASA SC(2)-0606 AIRFOIL | NASA SC(2)-0606 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.3% at 81% chord | Remove Airfoil details Airfoil plotter |
(s3010-il) S3010-103-84 | Selig S3010 low Reynolds number airfoil Max thickness 10.3% at 25% chord Max camber 2.3% at 43.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh114-il,sc20606-il,s3010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh114-il | 50,000 | 9 | 9.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 9 | 56.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 5 | 60.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 9 | 89.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 5 | 88.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 5 | 121 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 9 | 161 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 5 | 140.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20606-il | 50,000 | 9 | 23.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20606-il | 50,000 | 5 | 25.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20606-il | 100,000 | 9 | 31.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20606-il | 100,000 | 5 | 35 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20606-il | 200,000 | 9 | 51.8 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20606-il | 200,000 | 5 | 46.2 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20606-il | 500,000 | 9 | 72.4 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20606-il | 500,000 | 5 | 53.6 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20606-il | 1,000,000 | 9 | 82.1 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20606-il | 1,000,000 | 5 | 65.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3010-il | 50,000 | 9 | 28.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3010-il | 50,000 | 5 | 36.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3010-il | 100,000 | 9 | 50.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3010-il | 100,000 | 5 | 52.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3010-il | 200,000 | 9 | 70 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3010-il | 200,000 | 5 | 68.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3010-il | 500,000 | 9 | 95.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3010-il | 500,000 | 5 | 89.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3010-il | 1,000,000 | 9 | 113.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3010-il | 1,000,000 | 5 | 104.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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