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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(ag04-il) AG04 | Drela AG04 airfoil Max thickness 6.4% at 22.5% chord Max camber 1.7% at 41.5% chord | Remove Airfoil details Airfoil plotter |
(a18-il) A18 (original) | Archer A18 F1C free flight airfoil(original) Max thickness 7.3% at 30% chord Max camber 3.9% at 45% chord | Remove Airfoil details Airfoil plotter |
(a18sm-il) A18 (smoothed) | Archer A18 F1C free flight airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 3.8% at 49.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag04-il,a18-il,a18sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag04-il | 50,000 | 9 | 32 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 50,000 | 5 | 33.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 100,000 | 9 | 45.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 100,000 | 5 | 45.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 200,000 | 9 | 58.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 200,000 | 5 | 57 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 500,000 | 9 | 76.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 500,000 | 5 | 72.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag04-il | 1,000,000 | 9 | 90 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag04-il | 1,000,000 | 5 | 85 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 50,000 | 9 | 44 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 50,000 | 5 | 44.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 100,000 | 9 | 65 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 100,000 | 5 | 63.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 200,000 | 9 | 86.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 200,000 | 5 | 80.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 500,000 | 9 | 111.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 500,000 | 5 | 99.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18-il | 1,000,000 | 9 | 124.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18-il | 1,000,000 | 5 | 109.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 50,000 | 9 | 44.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 50,000 | 5 | 44.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 100,000 | 9 | 65.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 100,000 | 5 | 63.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 200,000 | 9 | 87 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 200,000 | 5 | 81.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 500,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 500,000 | 5 | 102.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 1,000,000 | 9 | 132.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 1,000,000 | 5 | 116 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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