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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(hq07-il) HQ 0/7 AIRFOIL | Quabeck HQ 0/7 R/C sailplane airfoil Max thickness 7% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s811-nr) NREL's S811 Airfoil | NREL HAWT airfoil S811 root Max thickness 26.3% at 27.4% chord Max camber 1.7% at 76.4% chord | Remove Airfoil details Airfoil plotter |
(pw106-pw) PW106 | Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.9% at 27.5% chord Max camber 2.1% at 27.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq07-il,s811-nr,pw106-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq07-il | 50,000 | 9 | 26.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 50,000 | 5 | 24.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 100,000 | 9 | 35.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 100,000 | 5 | 31.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 200,000 | 9 | 43.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 200,000 | 5 | 36.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 500,000 | 9 | 50.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 500,000 | 5 | 46.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq07-il | 1,000,000 | 9 | 59.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq07-il | 1,000,000 | 5 | 56.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 50,000 | 9 | 6.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 50,000 | 5 | 7.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 100,000 | 9 | 12.8 at α=15° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 100,000 | 5 | 28.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 200,000 | 9 | 48.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 200,000 | 5 | 52.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 500,000 | 9 | 79.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 500,000 | 5 | 76 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 1,000,000 | 9 | 99.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 1,000,000 | 5 | 90.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pw106-pw | 50,000 | 9 | 25 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 100,000 | 9 | 46.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 200,000 | 9 | 61.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 500,000 | 9 | 74.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 1,000,000 | 9 | 84.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 2,000,000 | 9 | 94.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw106-pw | 5,000,000 | 9 | 116.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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