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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(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 |
(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 |
(giiik-il) GIII BL369 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.5% at 25% chord | Remove Airfoil details Airfoil plotter |
(chen-il) CHEN AIRFOIL | University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(ag18-il) AG18 | Drela AG18 airfoil Max thickness 5.9% at 20.7% chord Max camber 2.2% at 44.1% chord | Remove Airfoil details Airfoil plotter |
(hor20-il) ONERA HOR20 AIRFOIL | Onera propeller blade airfoils from US Patent 4 Max thickness 20.4% at 24.3% chord Max camber 3.3% at 51.3% chord | Remove Airfoil details Airfoil plotter |
(glennmartin3-il) Glenn Martin 3 | Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord | Remove Airfoil details Airfoil plotter |
(s1012-il) S1012 | Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord Max camber 0% at 0% 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 |
(usa22-il) USA 22 AIRFOIL | USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(oaf117-il) OAF117 AIRFOIL | ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (n2414-il,rae103-il,giiik-il,chen-il,ag18-il,hor20-il,glennmartin3-il,s1012-il,n2415-il,usa22-il,oaf117-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| 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 | |
| giiik-il | 50,000 | 9 | 32.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 50,000 | 5 | 32 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 100,000 | 9 | 45.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 100,000 | 5 | 42.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 200,000 | 9 | 58 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 200,000 | 5 | 51.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 500,000 | 9 | 72.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 500,000 | 5 | 66.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiik-il | 1,000,000 | 9 | 79.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiik-il | 1,000,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 50,000 | 9 | 4.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 50,000 | 5 | 4.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 100,000 | 9 | 4.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 100,000 | 5 | 8.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 200,000 | 9 | 5.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 200,000 | 5 | 19.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 500,000 | 9 | 13.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 500,000 | 5 | 56.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 9 | 125.4 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 5 | 123 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 9 | 35.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 5 | 36.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 9 | 50.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 5 | 48.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 9 | 65.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 9 | 81.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 5 | 77 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 9 | 95.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 5 | 90.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 50,000 | 9 | 4.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 50,000 | 5 | 21.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 100,000 | 9 | 34.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 100,000 | 5 | 44.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 200,000 | 9 | 61.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 200,000 | 5 | 63.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 500,000 | 9 | 91.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 500,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 1,000,000 | 9 | 112.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 1,000,000 | 5 | 99.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 9 | 32.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 5 | 29.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 9 | 41.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 5 | 38.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 9 | 54.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 5 | 47.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 9 | 62.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 9 | 78.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 5 | 78.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 50,000 | 5 | 25.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 100,000 | 9 | 37.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 100,000 | 5 | 31.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 200,000 | 9 | 37.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 200,000 | 5 | 40 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 500,000 | 9 | 53.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 500,000 | 5 | 56.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 1,000,000 | 9 | 69.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 1,000,000 | 5 | 70.3 at α=9.75° | 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 | |
| usa22-il | 50,000 | 9 | 32.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 100,000 | 9 | 53.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 100,000 | 5 | 55.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 200,000 | 9 | 73 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 200,000 | 5 | 73.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 500,000 | 9 | 99.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 500,000 | 5 | 96.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 1,000,000 | 9 | 119.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 1,000,000 | 5 | 112.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 9 | 28.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 9 | 46.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 5 | 49.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 9 | 64.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 5 | 63 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 9 | 96.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 5 | 89.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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