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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(s2055-il) S2055 | Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(k3-il) GRUMMAN K-3 AIRFOIL | Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord | Remove Airfoil details Airfoil plotter |
(hq010-il) HQ 0/10 AIRFOIL | Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s2055-il,k3-il,hq010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2055-il | 50,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 5 | 35.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 9 | 51.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 5 | 48.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 9 | 70.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 5 | 61.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 9 | 92.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 5 | 71.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 9 | 95.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 5 | 81 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 50,000 | 9 | 24.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 50,000 | 5 | 23 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 100,000 | 9 | 30.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 100,000 | 5 | 33.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 200,000 | 9 | 49.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 200,000 | 5 | 50.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 500,000 | 9 | 79.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 500,000 | 5 | 65.9 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 9 | 94.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 5 | 70.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 50,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 50,000 | 5 | 27.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 100,000 | 9 | 39.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 100,000 | 5 | 36 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 200,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 200,000 | 5 | 41.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 500,000 | 9 | 54.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 500,000 | 5 | 56.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 1,000,000 | 9 | 71 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 1,000,000 | 5 | 70.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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