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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(naca2415-il) NACA 2415 | NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(usa25-il) USA 25 AIRFOIL | USA-25 airfoil Max thickness 8.3% at 19.9% chord Max camber 5.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(hq2511-il) HQ 2.5/11 AIRFOIL | Quabeck HQ 2.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(ah93k130-il) AH 93-K-130/15 | Althaus AH 93-K-130/15 airfoil for use with flaps (K) Max thickness 13.1% at 42% chord Max camber 3.5% at 42% chord | Remove Airfoil details Airfoil plotter |
(naca16012-il) NACA 16-012 | NACA 16-012 airfoil Max thickness 12% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(usa98-il) USA 98 AIRFOIL | USA-98 airfoil Max thickness 14.3% at 30% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(usa34-il) USA 34 AIRFOIL | USA-34 airfoil Max thickness 18% at 29.5% chord Max camber 7.7% at 39.5% chord | Remove Airfoil details Airfoil plotter |
(naca4412-il) NACA 4412 | NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca63206-il) NACA 63-206 | NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(usa49-il) USA 49 AIRFOIL | USA-49 airfoil Max thickness 7.3% at 30% chord Max camber 1.7% at 30% chord | Remove Airfoil details Airfoil plotter |
(usa40-il) USA 40 AIRFOIL | USA-40 airfoil Max thickness 13.3% at 30% chord Max camber 4.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(hq1585-il) HQ 1.5/8.5 AIRFOIL | Quabeck HQ 1.5/8.5 R/C sailplane airfoil Max thickness 8.6% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca63209-il) NACA 63-209 | NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq1010-il) HQ 1.0/10 AIRFOIL | Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca2415-il,usa25-il,hq2511-il,ah93k130-il,naca16012-il,usa98-il,usa34-il,naca4412-il,naca63206-il,usa49-il,usa40-il,hq1585-il,naca63209-il,hq1010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2415-il | 50,000 | 9 | 27.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 50,000 | 5 | 31.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 100,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 100,000 | 5 | 47.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 200,000 | 9 | 64.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 200,000 | 5 | 61.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 500,000 | 9 | 86.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 500,000 | 5 | 79.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2415-il | 1,000,000 | 9 | 102.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2415-il | 1,000,000 | 5 | 88.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 50,000 | 9 | 25.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 50,000 | 5 | 35.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 100,000 | 9 | 52.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 100,000 | 5 | 54.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 200,000 | 9 | 74.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 200,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 500,000 | 9 | 102 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 500,000 | 5 | 97.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 1,000,000 | 9 | 124.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 1,000,000 | 5 | 106.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 50,000 | 9 | 35.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 50,000 | 5 | 37.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 100,000 | 9 | 56.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 100,000 | 5 | 54.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 200,000 | 9 | 78.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 200,000 | 5 | 70.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 500,000 | 9 | 102.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 500,000 | 5 | 84.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2511-il | 1,000,000 | 9 | 107.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2511-il | 1,000,000 | 5 | 92.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k130-il | 50,000 | 9 | 25.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k130-il | 50,000 | 5 | 22.6 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k130-il | 100,000 | 9 | 42.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k130-il | 100,000 | 5 | 40.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k130-il | 200,000 | 9 | 75.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k130-il | 200,000 | 5 | 73.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k130-il | 500,000 | 9 | 114.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k130-il | 500,000 | 5 | 104.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k130-il | 1,000,000 | 9 | 136.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k130-il | 1,000,000 | 5 | 108.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 50,000 | 9 | 21.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 50,000 | 5 | 22.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 100,000 | 9 | 28.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 100,000 | 5 | 30.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 200,000 | 9 | 44.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 200,000 | 5 | 32.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 500,000 | 9 | 42.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 500,000 | 5 | 44.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16012-il | 1,000,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16012-il | 1,000,000 | 5 | 55.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 9 | 8.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 5 | 26.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 9 | 54.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 5 | 59.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 9 | 84.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 5 | 84.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 9 | 120.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 5 | 112.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 9 | 147.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 5 | 124.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 50,000 | 9 | 4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 50,000 | 5 | 9.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 100,000 | 9 | 9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 100,000 | 5 | 40.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 200,000 | 9 | 66.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 200,000 | 5 | 60.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 500,000 | 9 | 86.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 500,000 | 5 | 75 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 1,000,000 | 9 | 104.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 1,000,000 | 5 | 87.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 9 | 33.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 50,000 | 5 | 36.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 9 | 56.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 200,000 | 5 | 76.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 500,000 | 5 | 101.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 9 | 129.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4412-il | 1,000,000 | 5 | 119.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 9 | 24.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 50,000 | 5 | 31.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 9 | 43.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 100,000 | 5 | 41.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 9 | 57 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 200,000 | 5 | 52.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 9 | 72.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 500,000 | 5 | 58.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 9 | 80.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63206-il | 1,000,000 | 5 | 69 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 50,000 | 9 | 33.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 50,000 | 5 | 33.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 100,000 | 9 | 43.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 100,000 | 5 | 42.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 200,000 | 9 | 52.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 200,000 | 5 | 48.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 500,000 | 9 | 59.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 500,000 | 5 | 65.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 1,000,000 | 9 | 78 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 1,000,000 | 5 | 75.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 50,000 | 9 | 23.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 50,000 | 5 | 35.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 100,000 | 9 | 50.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 100,000 | 5 | 53.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 200,000 | 9 | 71.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 200,000 | 5 | 69.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 500,000 | 9 | 95.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 500,000 | 5 | 82.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 1,000,000 | 9 | 105.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 1,000,000 | 5 | 87 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 50,000 | 9 | 35.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 100,000 | 9 | 51.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 100,000 | 5 | 48.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 200,000 | 9 | 67.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 200,000 | 5 | 58.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 500,000 | 9 | 84.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 500,000 | 5 | 67.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 1,000,000 | 9 | 85.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 1,000,000 | 5 | 80.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 50,000 | 9 | 32.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 50,000 | 5 | 32.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 100,000 | 9 | 47.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 100,000 | 5 | 44.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 200,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 200,000 | 5 | 55.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 500,000 | 9 | 78 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 500,000 | 5 | 63.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca63209-il | 1,000,000 | 9 | 84.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca63209-il | 1,000,000 | 5 | 72.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 9 | 32.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 5 | 45.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 9 | 63.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 5 | 55.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 9 | 79.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 5 | 68.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 9 | 85.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 5 | 78 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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