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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(n2415-il) NACA 2415 | NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(oa212-il) ONERA OA212 AIRFOIL | ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord | Remove Airfoil details Airfoil plotter |
(oa213-il) ONERA OA213 AIRFOIL | ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord | Remove Airfoil details Airfoil plotter |
(n2h15-il) NACA 2-H-15 AIRFOIL | NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(n2414-il) NACA 2414 | NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (n2415-il,oa212-il,oa213-il,n2h15-il,n2414-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n2415-il | 50,000 | 9 | 26.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 50,000 | 5 | 31.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 100,000 | 9 | 46.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 100,000 | 5 | 47.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 200,000 | 9 | 64.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 200,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 500,000 | 9 | 87.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 500,000 | 5 | 79.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2415-il | 1,000,000 | 9 | 103 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2415-il | 1,000,000 | 5 | 89.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 50,000 | 9 | 26.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 50,000 | 5 | 31.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 100,000 | 9 | 44.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 100,000 | 5 | 45.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 200,000 | 9 | 60.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 200,000 | 5 | 59.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 500,000 | 9 | 82.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 500,000 | 5 | 76.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa212-il | 1,000,000 | 9 | 96.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa212-il | 1,000,000 | 5 | 87 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 9 | 26.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 5 | 29.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 9 | 54 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 9 | 75.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 5 | 75.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 9 | 95.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 9 | 18.1 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 5 | 13.4 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 9 | 20 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 5 | 20.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 9 | 34.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 5 | 38.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 9 | 110.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 5 | 107.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 9 | 145.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 5 | 122.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 50,000 | 9 | 29.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 50,000 | 5 | 32.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 100,000 | 9 | 47.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 100,000 | 5 | 48.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 200,000 | 9 | 65.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 200,000 | 5 | 62.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 500,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 500,000 | 5 | 79.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2414-il | 1,000,000 | 9 | 103.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2414-il | 1,000,000 | 5 | 90 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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