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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(naca0018-il) NACA 0018 | NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(n1h15-il) NACA 1-H-15 AIRFOIL | NACA 1-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca2408-il) NACA 2408 | NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(npl9615-il) NPL 9615 AIRFOIL | NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca0018-il,n1h15-il,naca2408-il,npl9615-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0018-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 50,000 | 5 | 26.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 9 | 37.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 100,000 | 5 | 38.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 9 | 50.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 200,000 | 5 | 48 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 9 | 65.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 500,000 | 5 | 61.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 9 | 77.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0018-il | 1,000,000 | 5 | 73.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 50,000 | 9 | 18.6 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 50,000 | 5 | 12.6 at α=15.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 100,000 | 9 | 20.3 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 100,000 | 5 | 19.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 200,000 | 9 | 29 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 200,000 | 5 | 31.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 500,000 | 9 | 103.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 500,000 | 5 | 102.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 1,000,000 | 9 | 150.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 1,000,000 | 5 | 133.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 50,000 | 9 | 37.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 50,000 | 5 | 36.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 9 | 52.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 5 | 48.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 9 | 66.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 5 | 58.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 9 | 80.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 5 | 67.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 9 | 86.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 5 | 82.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 9 | 29 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 5 | 30.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 5 | 42.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 9 | 70.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 5 | 68.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 9 | 84.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 5 | 77.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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