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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(fx76120-il) WORTMANN FX 76-120 | Wortmann FX 76-120 symmetrical airfoil Max thickness 12.1% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(npl9510-il) NPL 9510 AIRFOIL | NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord | Remove Airfoil details Airfoil plotter |
(fx69274-il) WORTMANN FX 69-274 | Wortmann FX 69-274 airfoil Max thickness 27.4% at 33.9% chord Max camber 3.2% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(drgnfly-il) DRAGONFLY CANARD | Dragonfly Canard airfoil Max thickness 19.3% at 37.6% chord Max camber 6.6% at 40.9% chord | Remove Airfoil details Airfoil plotter |
(ah95160-il) AH 95-160 | Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord Max camber 5.6% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(fx61163-il) FX 61-163 AIRFOIL | Wortmann FX 61-163 airfoil Max thickness 16.4% at 37.1% chord Max camber 2.6% at 33.9% 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 |
(nacam18-il) NACA M18 | NACA M18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx76120-il,npl9510-il,fx69274-il,drgnfly-il,ah95160-il,fx61163-il,amsoil1-il,nacam18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx76120-il | 50,000 | 9 | 25 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76120-il | 50,000 | 5 | 26.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76120-il | 100,000 | 9 | 35.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76120-il | 100,000 | 5 | 37.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76120-il | 200,000 | 9 | 49.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76120-il | 200,000 | 5 | 49.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76120-il | 500,000 | 9 | 67.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76120-il | 500,000 | 5 | 64.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx76120-il | 1,000,000 | 9 | 78.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx76120-il | 1,000,000 | 5 | 76.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 50,000 | 9 | 15.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 50,000 | 5 | 17 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 100,000 | 9 | 18.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 100,000 | 5 | 23.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 200,000 | 9 | 25.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 200,000 | 5 | 32.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 500,000 | 9 | 40.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 500,000 | 5 | 49.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 1,000,000 | 9 | 57.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 1,000,000 | 5 | 67.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69274-il | 50,000 | 9 | 1.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 100,000 | 9 | 1.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 200,000 | 9 | 36 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 500,000 | 9 | 65.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69274-il | 1,000,000 | 9 | 81.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 50,000 | 9 | 3.9 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 50,000 | 5 | 5.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 100,000 | 9 | 4.7 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 100,000 | 5 | 8.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 200,000 | 9 | 8.8 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 200,000 | 5 | 45.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 500,000 | 9 | 87.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 500,000 | 5 | 104.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 1,000,000 | 9 | 144.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 1,000,000 | 5 | 149.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 50,000 | 9 | 5.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 50,000 | 5 | 12.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 9 | 23.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 5 | 24.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 9 | 65.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 5 | 73.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 9 | 130.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 5 | 128.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 9 | 173.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 5 | 163.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 50,000 | 9 | 6.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 50,000 | 5 | 19.4 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 9 | 47.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 5 | 50 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 9 | 70.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 9 | 103.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 5 | 98.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 5 | 115.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 0 | 127.4 at α=5.75° | Mach=0 Ncrit=9 | 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 | |
| nacam18-il | 50,000 | 9 | 10.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 50,000 | 5 | 26.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 100,000 | 9 | 47.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 100,000 | 5 | 50.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 200,000 | 9 | 71.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 200,000 | 5 | 72.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 500,000 | 9 | 102.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 500,000 | 5 | 99.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 1,000,000 | 9 | 125.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 1,000,000 | 5 | 114 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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