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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(raf28-il) RAF 28 AIRFOIL | RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc12n1-il) NASA/LANGLEY RC-12(N)1 AIRFOIL | NASA/Langley RC-12(N)1 rotorcraft airfoil Max thickness 12% at 37.4% chord Max camber 1.4% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf28-il,rc12n1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf28-il | 50,000 | 9 | 35.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 50,000 | 5 | 35.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 9 | 52.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 5 | 50.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 9 | 69.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 5 | 64.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 9 | 90.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 5 | 79.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 9 | 103.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 5 | 83.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 50,000 | 9 | 32 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 50,000 | 5 | 31.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 100,000 | 9 | 49.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 100,000 | 5 | 47.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 200,000 | 9 | 66.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 200,000 | 5 | 61 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 500,000 | 9 | 86.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 500,000 | 5 | 70.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 1,000,000 | 9 | 92.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 1,000,000 | 5 | 76.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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