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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(goe802b-il) GOE 802 B AIRFOIL | Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(s3002-il) SELIG 3002-099-83 | Selig S3002 low Reynolds number airfoil Max thickness 9.9% at 30.6% chord Max camber 2.3% at 49.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe802b-il,s3002-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe802b-il | 50,000 | 9 | 26.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 50,000 | 5 | 39.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 100,000 | 9 | 53.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 100,000 | 5 | 60.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 200,000 | 9 | 76.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 200,000 | 5 | 73.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 500,000 | 9 | 104.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 500,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe802b-il | 1,000,000 | 9 | 105.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe802b-il | 1,000,000 | 5 | 103.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 50,000 | 9 | 35.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 50,000 | 5 | 39.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 100,000 | 9 | 56.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 100,000 | 5 | 55.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 200,000 | 9 | 76.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 200,000 | 5 | 70.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 500,000 | 9 | 99.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 500,000 | 5 | 89.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 1,000,000 | 9 | 112.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 1,000,000 | 5 | 100.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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