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 | ||
(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 |
(s4094-il) S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) | Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 9.9% at 29.1% chord Max camber 1.8% at 33.6% chord | Remove Airfoil details Airfoil plotter |
(s3024-il) AIRFOIL 3024 9.84% | Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s3-il,s4094-il,s3024-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| s4094-il | 50,000 | 9 | 29.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4094-il | 50,000 | 5 | 34.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4094-il | 100,000 | 9 | 44.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4094-il | 100,000 | 5 | 47.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4094-il | 200,000 | 9 | 59.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4094-il | 200,000 | 5 | 58.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4094-il | 500,000 | 9 | 76.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4094-il | 500,000 | 5 | 73.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4094-il | 1,000,000 | 9 | 87.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4094-il | 1,000,000 | 5 | 82.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 50,000 | 9 | 34.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 50,000 | 5 | 38.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 100,000 | 9 | 57.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 100,000 | 5 | 57.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 200,000 | 9 | 80.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 200,000 | 5 | 76.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 500,000 | 9 | 110.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 500,000 | 5 | 96.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3024-il | 1,000,000 | 9 | 129 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3024-il | 1,000,000 | 5 | 110.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||