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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(naca2408-il) NACA 2408 | NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe278-il) GOE 278 (DAIMLER IX) AIRFOIL | Gottingen 278 (DAIMLER IX) airfoil Max thickness 7.4% at 29.9% chord Max camber 4.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(ah94145-il) AH 94-145 | Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord Max camber 5.6% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(raf25-il) RAF 25 AIRFOIL | RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca2408-il,goe278-il,ah94145-il,raf25-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2408-il | 50,000 | 9 | 37.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 50,000 | 5 | 36.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 9 | 52.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 5 | 48.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 9 | 66.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 5 | 58.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 9 | 80.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 5 | 67.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 9 | 86.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 5 | 82.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 50,000 | 9 | 38.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 50,000 | 5 | 40.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 100,000 | 9 | 55.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 200,000 | 9 | 72.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 200,000 | 5 | 72.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 500,000 | 9 | 95.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 500,000 | 5 | 92.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 1,000,000 | 9 | 113.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 1,000,000 | 5 | 102.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 50,000 | 9 | 6.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 50,000 | 5 | 14.8 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 9 | 28 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 5 | 30.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 9 | 75.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 5 | 81.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 9 | 135.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 5 | 132.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 9 | 177.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 5 | 164.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 50,000 | 5 | 30.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 9 | 43.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 5 | 40.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 9 | 56.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 5 | 47.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 9 | 68.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 5 | 55.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 9 | 72.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 5 | 68.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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