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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(goe116-il) GOE 116 (MVA MK.3) AIRFOIL | Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(s3025-il) S3025 9.38% | Selig S3025 low Reynolds number airfoil Max thickness 9.4% at 30.9% chord Max camber 3% at 44.9% chord | Remove Airfoil details Airfoil plotter |
(goe06k-il) GOE 6K AIRFOIL | Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(fx75193-il) WORTMANN FX 75-193 | Wortmann FX 75-193 airfoil Max thickness 19.3% at 40.2% chord Max camber 3.7% at 69.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe116-il,s3025-il,goe06k-il,fx75193-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe116-il | 50,000 | 9 | 29.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 9 | 58 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 5 | 56.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 9 | 78.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 5 | 76.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 9 | 106.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 5 | 81.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 9 | 100.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 5 | 91.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 50,000 | 9 | 33.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 50,000 | 5 | 39.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 100,000 | 9 | 57 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 100,000 | 5 | 58.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 200,000 | 9 | 80 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 200,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 500,000 | 9 | 109.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 500,000 | 5 | 99.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3025-il | 1,000,000 | 9 | 130.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3025-il | 1,000,000 | 5 | 114.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 50,000 | 9 | 26.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 50,000 | 5 | 28.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 100,000 | 9 | 45.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 100,000 | 5 | 44.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 200,000 | 9 | 74.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 200,000 | 5 | 77 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 500,000 | 9 | 117.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 500,000 | 5 | 116.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe06k-il | 1,000,000 | 9 | 147.6 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe06k-il | 1,000,000 | 5 | 132.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 9 | 4.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 5 | 11.7 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 9 | 23.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 5 | 22.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 9 | 43.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 5 | 44.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 9 | 91.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 5 | 93.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 9 | 122.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 5 | 120.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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