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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(s834-nr) NREL's S834 Airfoil | NREL HAWT airfoil S834 tip 15.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.00 Clmax(R)=1.02 High max lift coef Max thickness 15% at 39.5% chord Max camber 1.6% at 60% chord | Remove Airfoil details Airfoil plotter |
(goe113-il) GOE 113 AIRFOIL | Gottingen 113 airfoil Max thickness 6.7% at 30% chord Max camber 3% at 40% 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 |
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Polars for (s834-nr,goe113-il,goe228-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s834-nr | 50,000 | 9 | 29.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s834-nr | 50,000 | 5 | 26.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s834-nr | 100,000 | 9 | 47.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s834-nr | 100,000 | 5 | 44.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s834-nr | 200,000 | 9 | 70.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s834-nr | 200,000 | 5 | 55.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s834-nr | 500,000 | 9 | 81.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s834-nr | 500,000 | 5 | 74.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s834-nr | 1,000,000 | 9 | 102.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s834-nr | 1,000,000 | 5 | 83.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 50,000 | 9 | 37.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 50,000 | 5 | 40 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 100,000 | 9 | 54.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 100,000 | 5 | 54.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 200,000 | 9 | 70 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 200,000 | 5 | 66.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 500,000 | 9 | 86.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 500,000 | 5 | 78 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe113-il | 1,000,000 | 9 | 97.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe113-il | 1,000,000 | 5 | 83.3 at α=3.75° | 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 | |
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