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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(rg149-il) RG 14 9% AIRFOIL | Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord | Remove Airfoil details Airfoil plotter |
(raf28-il) RAF 28 AIRFOIL | RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(rg8-il) RG 8 AIRFOIL | Rolf Girsberger RG 8 airfoil Max thickness 10.8% at 31.1% chord Max camber 2.2% at 60.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rg149-il,raf28-il,rg8-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg149-il | 50,000 | 9 | 33.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 50,000 | 5 | 34.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 9 | 48.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 100,000 | 5 | 46.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 9 | 63.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 200,000 | 5 | 57.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 9 | 81.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 500,000 | 5 | 70.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 9 | 90 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg149-il | 1,000,000 | 5 | 84.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 50,000 | 9 | 35.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 50,000 | 5 | 35.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 9 | 52.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 5 | 50.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 9 | 69.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 5 | 64.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 9 | 90.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 5 | 79.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 9 | 103.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 5 | 83.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 50,000 | 9 | 35.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 50,000 | 5 | 37.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 100,000 | 9 | 54.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 100,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 200,000 | 9 | 73.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 200,000 | 5 | 68.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 500,000 | 9 | 96.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 500,000 | 5 | 83.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg8-il | 1,000,000 | 9 | 107.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg8-il | 1,000,000 | 5 | 92.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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