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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(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL | Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx69h098-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx69h098-il | 50,000 | 9 | 27.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 50,000 | 5 | 31.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 100,000 | 9 | 43.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 100,000 | 5 | 45.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 200,000 | 9 | 59.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 200,000 | 5 | 59.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 500,000 | 9 | 81.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 500,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 1,000,000 | 9 | 98.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 1,000,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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