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 | ||
(bacnlf-il) BOEING HSNLF AIRFOIL | Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord | Remove Airfoil details Airfoil plotter |
(avistar-il) AVISTAR | Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (bacnlf-il,avistar-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacnlf-il | 50,000 | 9 | 26.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 9 | 35.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 5 | 40.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 9 | 55.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 5 | 53 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 9 | 78.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 5 | 64.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 9 | 88.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 5 | 66.1 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 50,000 | 9 | 30.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 50,000 | 5 | 31.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 100,000 | 9 | 49.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 100,000 | 5 | 46.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 200,000 | 9 | 63.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 200,000 | 5 | 59.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 500,000 | 9 | 81.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 500,000 | 5 | 72 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| avistar-il | 1,000,000 | 9 | 93.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| avistar-il | 1,000,000 | 5 | 71.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||