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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(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL | NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord | Remove Airfoil details Airfoil plotter |
(raf69-il) RAF 69 AIRFOIL | RAF-69 airfoil Max thickness 20.6% at 30% chord Max camber 1.7% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rc08b3-il,raf69-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc08b3-il | 50,000 | 9 | 32.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 50,000 | 5 | 31.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 100,000 | 9 | 45.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 100,000 | 5 | 41.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 200,000 | 9 | 57.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 200,000 | 5 | 49.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 500,000 | 9 | 67.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 500,000 | 5 | 60 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08b3-il | 1,000,000 | 9 | 71.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08b3-il | 1,000,000 | 5 | 73.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf69-il | 50,000 | 9 | 4.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf69-il | 50,000 | 5 | 18.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf69-il | 100,000 | 9 | 40.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf69-il | 100,000 | 5 | 40.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf69-il | 200,000 | 9 | 58.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf69-il | 200,000 | 5 | 51.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf69-il | 500,000 | 9 | 74 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf69-il | 500,000 | 5 | 63.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf69-il | 1,000,000 | 9 | 88.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf69-il | 1,000,000 | 5 | 72.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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