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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(n5h20-il) NACA 5-H-20 AIRFOIL | NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(e174-il) E174 (Dicke 8.92%) | Eppler E174 low Reynolds number airfoil Max thickness 8.9% at 31.2% chord Max camber 3.3% at 44.9% chord | Remove Airfoil details Airfoil plotter |
(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 |
(m25-il) NACA M25 AIRFOIL | NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(naca23015-il) NACA 23015 | NACA 23015 airfoil Max thickness 15% at 30% chord Max camber 1.8% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n5h20-il,e174-il,n2415-il,m25-il,naca23015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n5h20-il | 50,000 | 9 | 3.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 50,000 | 5 | 7.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 100,000 | 9 | 17 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 100,000 | 5 | 14.8 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 200,000 | 9 | 25.4 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 200,000 | 5 | 34.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 500,000 | 9 | 78.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 500,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 1,000,000 | 9 | 85.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 1,000,000 | 5 | 75.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 50,000 | 9 | 38.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 50,000 | 5 | 39 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 100,000 | 9 | 61.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 100,000 | 5 | 61.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 200,000 | 9 | 84.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 200,000 | 5 | 83 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 500,000 | 9 | 117.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 500,000 | 5 | 110.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 1,000,000 | 9 | 141.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 1,000,000 | 5 | 128.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| m25-il | 50,000 | 9 | 6.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 50,000 | 5 | 20.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 100,000 | 9 | 53.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 100,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 200,000 | 9 | 78.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 200,000 | 5 | 78.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 500,000 | 9 | 102.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 500,000 | 5 | 94.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 9 | 111.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 5 | 107.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 50,000 | 9 | 21 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 50,000 | 5 | 27.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 100,000 | 9 | 33.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 100,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 200,000 | 9 | 48.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 200,000 | 5 | 52.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 500,000 | 9 | 72 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 500,000 | 5 | 74.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 1,000,000 | 9 | 91 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 1,000,000 | 5 | 91.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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