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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(s814-nr) NREL's S814 Airfoil | NREL HAWT airfoil S814 root 24.0% Dia=20 to 30 m Re=1.5E+6 Clmax(S)=1.56 Clmax(R)=1.51 High max lift coef Max thickness 24.1% at 28.4% chord Max camber 3% at 74.5% chord | Remove Airfoil details Airfoil plotter |
(hq2010-il) HQ 2.0/10 AIRFOIL | Quabeck HQ 2.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2% at 45% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s814-nr,hq2010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s814-nr | 50,000 | 9 | 4.4 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 50,000 | 5 | 10.9 at α=14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 100,000 | 9 | 35.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 100,000 | 5 | 40.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 200,000 | 9 | 58.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 200,000 | 5 | 58.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 500,000 | 9 | 84.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 500,000 | 5 | 80.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 1,000,000 | 9 | 104.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 1,000,000 | 5 | 97.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2010-il | 50,000 | 9 | 35.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2010-il | 50,000 | 5 | 37 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2010-il | 100,000 | 9 | 54.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2010-il | 100,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2010-il | 200,000 | 9 | 73.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2010-il | 200,000 | 5 | 67.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2010-il | 500,000 | 9 | 97.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2010-il | 500,000 | 5 | 78.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2010-il | 1,000,000 | 9 | 102.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2010-il | 1,000,000 | 5 | 86.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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