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 | ||
(s825-nr) NREL's S825 Airfoil | NREL HAWT airfoil S825 primary 17.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=1.44 Clmax(R)=1.37 High max lift coef Max thickness 17.1% at 29.9% chord Max camber 3.9% at 65.3% chord | Remove Airfoil details Airfoil plotter |
(s8036-il) S8036 (16%) | Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% chord | Remove Airfoil details Airfoil plotter |
(goe228-il) GOE 228 (MVA H.38) AIRFOIL | Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% chord | Remove Airfoil details Airfoil plotter |
(goe562-il) GOE 562 AIRFOIL | Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe57-il) GOE 57 AIRFOIL | Gottingen 57 airfoil Max thickness 6.3% at 19.9% chord Max camber 5.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s825-nr,s8036-il,goe228-il,goe562-il,goe57-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s825-nr | 50,000 | 9 | 29.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 50,000 | 5 | 32.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 100,000 | 9 | 50.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 100,000 | 5 | 52.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 200,000 | 9 | 70.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 200,000 | 5 | 70.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 500,000 | 9 | 97.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 500,000 | 5 | 94 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 1,000,000 | 9 | 118.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 1,000,000 | 5 | 111 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 50,000 | 9 | 26.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 50,000 | 5 | 25.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 100,000 | 9 | 48.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 100,000 | 5 | 48 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 200,000 | 9 | 70.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 200,000 | 5 | 61.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 500,000 | 9 | 87.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 500,000 | 5 | 73.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8036-il | 1,000,000 | 9 | 99.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8036-il | 1,000,000 | 5 | 82.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 50,000 | 9 | 5.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 50,000 | 5 | 25.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 100,000 | 9 | 45.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 100,000 | 5 | 51.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 200,000 | 9 | 70.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 200,000 | 5 | 66.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 500,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 500,000 | 5 | 88.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 1,000,000 | 9 | 116.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 1,000,000 | 5 | 109 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 50,000 | 9 | 9.2 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 50,000 | 5 | 25.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 9 | 40.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 5 | 50 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 9 | 70.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 9 | 101.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 5 | 96.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 9 | 126.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 5 | 115.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 50,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 50,000 | 5 | 43.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 100,000 | 9 | 63.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 100,000 | 5 | 59.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 200,000 | 9 | 82.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 200,000 | 5 | 70.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 500,000 | 9 | 93 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 500,000 | 5 | 86.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 1,000,000 | 9 | 105.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 1,000,000 | 5 | 102.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||