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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(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 |
(s9033-il) S9033 (7.5%) | Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eh2010-il,s9033-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| s9033-il | 50,000 | 9 | 21.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 50,000 | 5 | 23.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 100,000 | 9 | 29.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 100,000 | 5 | 32.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 200,000 | 9 | 39.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 200,000 | 5 | 42.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 500,000 | 9 | 56.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 500,000 | 5 | 58.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 1,000,000 | 9 | 70.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 1,000,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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