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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(dsma523a-il) DSMA-523A AIRFOIL | McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge Max thickness 11% at 36% chord Max camber 2.3% at 82% 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 |
(dsma523b-il) DSMA-523B AIRFOIL | McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord | Remove Airfoil details Airfoil plotter |
(n6409-il) NACA6409 9% | NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (dsma523a-il,n2415-il,dsma523b-il,n6409-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dsma523a-il | 50,000 | 9 | 20.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 50,000 | 5 | 18.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 100,000 | 9 | 20.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 100,000 | 5 | 25.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 200,000 | 9 | 27.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 200,000 | 5 | 37.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 500,000 | 9 | 47.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 500,000 | 5 | 59.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523a-il | 1,000,000 | 9 | 70.3 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523a-il | 1,000,000 | 5 | 77.5 at α=7.5° | 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 | |
| dsma523b-il | 50,000 | 9 | 20.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 50,000 | 5 | 20.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 100,000 | 9 | 23.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 100,000 | 5 | 27.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 200,000 | 9 | 29.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 200,000 | 5 | 39.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 500,000 | 9 | 49.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 500,000 | 5 | 60 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 1,000,000 | 9 | 73.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 1,000,000 | 5 | 77.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 50,000 | 9 | 27.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 50,000 | 5 | 36 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 9 | 61.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 5 | 63.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 9 | 87.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 5 | 87.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 9 | 122.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 5 | 118.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 9 | 151 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 5 | 144.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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