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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(v43012-il) BOEING VERTOL V43012-1.58 AIRFOIL | Boeing-Vertol V43012-1.58 rotorcraft airfoil Max thickness 12% at 32% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL | Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord | Remove Airfoil details Airfoil plotter |
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(clarkw-il) CLARK W AIRFOIL | CLARK W airfoil Max thickness 11.2% at 30% chord Max camber 3.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(rae103-il) RAE 103 AIRFOIL | RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (v43012-il,v13009-il,v43015-il,clarkw-il,rae103-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v43012-il | 50,000 | 9 | 24 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 50,000 | 5 | 28.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 100,000 | 9 | 36.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 100,000 | 5 | 40.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 200,000 | 9 | 50.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 200,000 | 5 | 55.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 500,000 | 9 | 77.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 500,000 | 5 | 81.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43012-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43012-il | 1,000,000 | 5 | 101.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 50,000 | 5 | 28.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 9 | 36.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 5 | 39.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 9 | 49.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 5 | 53.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 9 | 72.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 5 | 71.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 9 | 88.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 5 | 86.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 50,000 | 9 | 32.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 50,000 | 5 | 36.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 100,000 | 9 | 53.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 200,000 | 9 | 73.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 200,000 | 5 | 69.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 500,000 | 9 | 98.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 500,000 | 5 | 91.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 1,000,000 | 9 | 116.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 1,000,000 | 5 | 107.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 50,000 | 9 | 27.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 50,000 | 5 | 27.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 100,000 | 9 | 40.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 100,000 | 5 | 36.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 200,000 | 9 | 48.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 200,000 | 5 | 39.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 500,000 | 9 | 54.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 500,000 | 5 | 52.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae103-il | 1,000,000 | 9 | 62.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae103-il | 1,000,000 | 5 | 66 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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