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 |
(ms317-il) NASA/LANGLEY MS(1)-0317 AIRFOIL | NASA/Langley MS(1)-0317 general aviation airfoil Max thickness 17% at 37.5% chord Max camber 1.7% at 72.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9033-il,ms317-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 | |
| ms317-il | 50,000 | 9 | 28.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 50,000 | 5 | 24.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 100,000 | 9 | 36.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 100,000 | 5 | 35.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 200,000 | 9 | 48.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 200,000 | 5 | 47.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 500,000 | 9 | 69.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 500,000 | 5 | 64.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 1,000,000 | 9 | 80.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 1,000,000 | 5 | 80.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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