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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(ah85l120-il) AH 85-L-120/17 | Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(eh2010-il) EH 2.0/10 | John Yost EH 2.0/10 for tailless R/C aircraft Max thickness 10.1% at 28.7% chord Max camber 2% at 25.9% chord | Remove Airfoil details Airfoil plotter |
(goe81-il) GOE 81 AIRFOIL | Gottingen 81 airfoil Max thickness 7.4% at 29.9% chord Max camber 6.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(e554-il) EPPLER 554 AIRFOIL | Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord Max camber 2.7% at 56.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah85l120-il,eh2010-il,goe81-il,e554-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah85l120-il | 50,000 | 9 | 21.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 50,000 | 5 | 27.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 9 | 37.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 5 | 29.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 200,000 | 5 | 35 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 9 | 48.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 5 | 43.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 9 | 55.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 50,000 | 9 | 19.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 50,000 | 5 | 30.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 100,000 | 9 | 46.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 100,000 | 5 | 47.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 200,000 | 9 | 63.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 200,000 | 5 | 63 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 500,000 | 9 | 87.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 500,000 | 5 | 83.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 1,000,000 | 9 | 106.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 1,000,000 | 5 | 94.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 50,000 | 9 | 31.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 50,000 | 5 | 42.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 100,000 | 9 | 61.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 100,000 | 5 | 65.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 200,000 | 9 | 89.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 200,000 | 5 | 83.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 500,000 | 9 | 114.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 500,000 | 5 | 102.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe81-il | 1,000,000 | 9 | 133.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe81-il | 1,000,000 | 5 | 104.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 50,000 | 5 | 18.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 100,000 | 9 | 36.4 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 100,000 | 5 | 46.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 200,000 | 9 | 69 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 200,000 | 5 | 70.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 500,000 | 9 | 103.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 500,000 | 5 | 98.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 9 | 127.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 5 | 118.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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