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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(n11h9-il) NACA 11-H-09 AIRFOIL | NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord Max camber 4.5% at 30% chord | Remove Airfoil details Airfoil plotter |
(lwk79100-il) LWK 79-100 | LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(l1003-il) LIEBECK L1003 AIRFOIL | Liebeck high lift airfoil Max thickness 17.7% at 30% chord Max camber 6.5% at 30% chord | Remove Airfoil details Airfoil plotter |
(n12-il) N-12 | N-12 airfoil Max thickness 10.5% at 30% chord Max camber 0.2% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n11h9-il,lwk79100-il,l1003-il,n12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n11h9-il | 50,000 | 9 | 24.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 50,000 | 5 | 24.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 100,000 | 9 | 52.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 100,000 | 5 | 53.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 200,000 | 9 | 79.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 200,000 | 5 | 79.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 500,000 | 9 | 114.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 500,000 | 5 | 109.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11h9-il | 1,000,000 | 9 | 138.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11h9-il | 1,000,000 | 5 | 125 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 9 | 25.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 9 | 37.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 5 | 35.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 9 | 47.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 5 | 44.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 5 | 60.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 9 | 72.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 5 | 74.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 9 | 4.1 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 50,000 | 5 | 5.2 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 9 | 4.5 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 100,000 | 5 | 7 at α=17.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 9 | 10.2 at α=18.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 200,000 | 5 | 10.1 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 9 | 74.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 500,000 | 5 | 68.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 9 | 104.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l1003-il | 1,000,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n12-il | 50,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n12-il | 50,000 | 5 | 27.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n12-il | 100,000 | 9 | 39 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n12-il | 100,000 | 5 | 36.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n12-il | 200,000 | 9 | 46.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n12-il | 200,000 | 5 | 42.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n12-il | 500,000 | 9 | 53.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n12-il | 500,000 | 5 | 55.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n12-il | 1,000,000 | 9 | 64.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n12-il | 1,000,000 | 5 | 73.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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