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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(s9033-il) S9033 (7.5%) | Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(sc20403-il) NASA SC(2)-0403 AIRFOIL | NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord | Remove Airfoil details Airfoil plotter |
(sc20518-il) NASA SC(2)-0518 AIRFOIL | NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9033-il,sc20403-il,sc20518-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s9033-il | 50,000 | 9 | 21.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 50,000 | 5 | 23.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 100,000 | 9 | 29.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 100,000 | 5 | 32.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 200,000 | 9 | 39.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 200,000 | 5 | 42.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 500,000 | 9 | 56.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 500,000 | 5 | 58.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9033-il | 1,000,000 | 9 | 70.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9033-il | 1,000,000 | 5 | 72 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20403-il | 50,000 | 9 | 18 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20403-il | 50,000 | 5 | 18 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20403-il | 100,000 | 9 | 24.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20403-il | 100,000 | 5 | 21.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20403-il | 200,000 | 9 | 32.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20403-il | 200,000 | 5 | 28.9 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20403-il | 500,000 | 9 | 42.4 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20403-il | 500,000 | 5 | 33.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20403-il | 1,000,000 | 9 | 46.5 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20403-il | 1,000,000 | 5 | 39.9 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 50,000 | 9 | 26 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 50,000 | 5 | 20.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 100,000 | 9 | 25.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 100,000 | 5 | 30.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 200,000 | 9 | 36.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 200,000 | 5 | 43.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 500,000 | 9 | 59.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 500,000 | 5 | 62.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20518-il | 1,000,000 | 9 | 77.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20518-il | 1,000,000 | 5 | 78.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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