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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(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL | Ryan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep) Max thickness 9.9% at 32.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(amsoil1-il) RUTAN CANARD AIRFOIL | Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord | Remove Airfoil details Airfoil plotter |
(clarky-il) CLARK Y AIRFOIL | CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord | Remove Airfoil details Airfoil plotter |
(clarkysm-il) CLARK-Y 11.7% smoothed | CLARK Y airfoil (smoothed) Max thickness 11.7% at 30.9% chord Max camber 3.5% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (bqm34-il,amsoil1-il,clarky-il,clarkysm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bqm34-il | 50,000 | 9 | 27.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bqm34-il | 50,000 | 5 | 26.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bqm34-il | 100,000 | 9 | 38.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bqm34-il | 100,000 | 5 | 34.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bqm34-il | 200,000 | 9 | 48.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bqm34-il | 200,000 | 5 | 42.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bqm34-il | 500,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bqm34-il | 500,000 | 5 | 58.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bqm34-il | 1,000,000 | 9 | 70.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bqm34-il | 1,000,000 | 5 | 72.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 50,000 | 9 | 33 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 50,000 | 5 | 31.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 9 | 48.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 5 | 46.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 9 | 67.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 5 | 59.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 9 | 86.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 5 | 68.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 9 | 93 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 5 | 81.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 50,000 | 9 | 29.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 9 | 73.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 5 | 69.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 9 | 98.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 5 | 90.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 9 | 114.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 5 | 108.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 50,000 | 9 | 30 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 50,000 | 5 | 35.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 100,000 | 9 | 52.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 100,000 | 5 | 53.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 200,000 | 9 | 74.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 200,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 500,000 | 9 | 101.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 500,000 | 5 | 90.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 1,000,000 | 9 | 119.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 1,000,000 | 5 | 106.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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