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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(griffith30symsuction-il) Griffith 30% Suction Airfoil | Griffith 30% suction airfoil Max thickness 30.6% at 49.3% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(goe803h-il) GOE 803 (HACKLINGER) AIRFOIL | Gottingen 803 (Hacklinger) airfoil Max thickness 6.3% at 15% chord Max camber 6.6% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (griffith30symsuction-il,goe803h-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| griffith30symsuction-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| griffith30symsuction-il | 50,000 | 5 | 10.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| griffith30symsuction-il | 100,000 | 9 | 17.2 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| griffith30symsuction-il | 100,000 | 5 | 11 at α=15.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| griffith30symsuction-il | 200,000 | 9 | 13.5 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| griffith30symsuction-il | 200,000 | 5 | 10.7 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| griffith30symsuction-il | 500,000 | 9 | 15 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| griffith30symsuction-il | 500,000 | 5 | 12.5 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| griffith30symsuction-il | 1,000,000 | 9 | 17.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| griffith30symsuction-il | 1,000,000 | 5 | 15.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 50,000 | 9 | 40 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 50,000 | 5 | 48.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 100,000 | 9 | 69.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 100,000 | 5 | 69.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 200,000 | 9 | 95.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 200,000 | 5 | 85.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 500,000 | 9 | 112.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 500,000 | 5 | 103.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 1,000,000 | 9 | 128.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 1,000,000 | 5 | 122.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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