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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(rae101-il) RAE 101 AIRFOIL | RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s2055-il) S2055 | Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(rae100-il) RAE 100 AIRFOIL | RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s3-il) REPUBLIC S-3 AIRFOIL | Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord Max camber 1.8% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rae101-il,s2055-il,rae100-il,s3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae101-il | 50,000 | 9 | 27.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 50,000 | 5 | 27.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 100,000 | 9 | 39 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 100,000 | 5 | 36.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 200,000 | 9 | 49.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 200,000 | 5 | 44.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 500,000 | 9 | 60.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 500,000 | 5 | 56.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 1,000,000 | 9 | 67.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 1,000,000 | 5 | 70.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 5 | 35.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 9 | 51.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 5 | 48.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 9 | 70.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 5 | 61.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 9 | 92.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 5 | 71.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 9 | 95.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 5 | 81 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 50,000 | 9 | 24.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 50,000 | 5 | 26.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 100,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 100,000 | 5 | 35.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 200,000 | 9 | 46.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 200,000 | 5 | 45 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 500,000 | 9 | 60.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 500,000 | 5 | 60.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae100-il | 1,000,000 | 9 | 74.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae100-il | 1,000,000 | 5 | 74.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 50,000 | 9 | 23.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 50,000 | 5 | 28.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 100,000 | 9 | 38.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 100,000 | 5 | 42.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 200,000 | 9 | 56.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 200,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 500,000 | 9 | 76.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 500,000 | 5 | 73.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 1,000,000 | 9 | 91.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 1,000,000 | 5 | 85.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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