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 | ||
(s3021-il) S3021-095-84 | Selig S3021 low Reynolds number airfoil Max thickness 9.5% at 30% chord Max camber 2.5% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(e336-il) EPPLER 336 AIRFOIL | Eppler E336 flying wing airfoil Max thickness 12.8% at 28.1% chord Max camber 2.8% at 23.4% chord | Remove Airfoil details Airfoil plotter |
(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL | Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord | Remove Airfoil details Airfoil plotter |
(s803-nr) NREL's S803 Airfoil | NREL HAWT airfoil S803 tip Not recommended Max thickness 11.5% at 37.5% chord Max camber 3.7% at 46.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s3021-il,e336-il,sc1012r8-il,s803-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3021-il | 50,000 | 9 | 32.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 50,000 | 5 | 37.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 100,000 | 9 | 53.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 100,000 | 5 | 55.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 200,000 | 9 | 74.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 200,000 | 5 | 71.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 500,000 | 9 | 101.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 500,000 | 5 | 91.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3021-il | 1,000,000 | 9 | 119.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3021-il | 1,000,000 | 5 | 105.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 50,000 | 9 | 16.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 50,000 | 5 | 25.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 100,000 | 9 | 35.7 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 100,000 | 5 | 44.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 200,000 | 9 | 61.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 200,000 | 5 | 62.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 500,000 | 9 | 87.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 500,000 | 5 | 78.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e336-il | 1,000,000 | 9 | 99 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e336-il | 1,000,000 | 5 | 96.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 9 | 23.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 9 | 34 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 5 | 37.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 9 | 46.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 5 | 50.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 5 | 72.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 9 | 88.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 5 | 90.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s803-nr | 50,000 | 9 | 38.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s803-nr | 50,000 | 5 | 37.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s803-nr | 100,000 | 9 | 63.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s803-nr | 100,000 | 5 | 63 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s803-nr | 200,000 | 9 | 89.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s803-nr | 200,000 | 5 | 83.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s803-nr | 500,000 | 9 | 118.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s803-nr | 500,000 | 5 | 108.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s803-nr | 1,000,000 | 9 | 140.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s803-nr | 1,000,000 | 5 | 124 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||