Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(s827-nr) NREL's S827 Airfoil | NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord | Remove Airfoil details Airfoil plotter |
(s823-nr) NREL's S823 Airfoil | NREL HAWT airfoil S823 root 21.0% Dia=2 to 10 m Re=4.0E+5 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.2% at 24.3% chord Max camber 2.4% at 70.5% chord | Remove Airfoil details Airfoil plotter |
(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 |
Drawing Options
Polars for (s827-nr,s823-nr,s814-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s827-nr | 50,000 | 9 | 16.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 50,000 | 5 | 14 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 100,000 | 9 | 20.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 100,000 | 5 | 21.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 200,000 | 9 | 35.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 200,000 | 5 | 35 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 500,000 | 9 | 84.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 500,000 | 5 | 81.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 1,000,000 | 9 | 121.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 1,000,000 | 5 | 109.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 50,000 | 9 | 20.9 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 50,000 | 5 | 20.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 100,000 | 9 | 42.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 100,000 | 5 | 43.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 200,000 | 9 | 62.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 200,000 | 5 | 60 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 500,000 | 9 | 86.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 500,000 | 5 | 77.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 1,000,000 | 9 | 101.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 1,000,000 | 5 | 87.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| Reynolds number calculator | |||||||