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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(coanda1-il) Coanda 1 | Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(bw3-il) Bergey BW-3 (smoothed) | Bergey BW-3 wind turbine airfoil (smoothed) Max thickness 5% at 7.4% chord Max camber 5.7% at 45.4% 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 |
(bacj-il) BOEING AIRFOIL J (no closed TE) | Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord Max camber 1.7% at 78% chord | Remove Airfoil details Airfoil plotter |
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Polars for (coanda1-il,bw3-il,avistar-il,bacj-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| coanda1-il | 50,000 | 9 | 38 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 50,000 | 5 | 37.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 100,000 | 9 | 54.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 100,000 | 5 | 47.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 200,000 | 9 | 60.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 200,000 | 5 | 45.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 500,000 | 9 | 63.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 500,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 1,000,000 | 9 | 60.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 1,000,000 | 5 | 57.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 50,000 | 9 | 46.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 50,000 | 5 | 46 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 100,000 | 9 | 67.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 100,000 | 5 | 58.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 200,000 | 9 | 74.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 200,000 | 5 | 68.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 500,000 | 9 | 88.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 500,000 | 5 | 79.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 1,000,000 | 9 | 98.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 1,000,000 | 5 | 89.2 at α=7.75° | 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 | |
| bacj-il | 50,000 | 9 | 20.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 50,000 | 5 | 20.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 9 | 27 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 5 | 25 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 9 | 31.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 5 | -1 at α=-100° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 500,000 | 9 | 51.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 1,000,000 | 9 | 61.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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