TL54


Direct link: TL54
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
TL54
Family: Lutz
Max thickness: 10.0% at x = 26.46% chord
Max camber: 2.4% at x = 33.83% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition

Notes:


Flying wing airfoil for F3B, F3F, F5B.
https://www.aerodesign.de/english/profile/profile_s.htm
Thorsten Lutz has developed the airfoil series TL54, TL55 and TL56 using Eppler Code. The airfoile series is already some years old, but has been hardly known in tailless scene. The difficult relations concerning stall behaviour on Tailless using different airfoils does normally not concern to the requirements of competition RC-Models. The potential benefite using different airfoils is minimal due to the flight behavior. Often it is so worse that just Tailless speed models use different airfoils. But even F5D designs normally use just one airfoil because cd optimization means reducing cd where cl requirement is small. And where is cl small? @Wingtip. What means stall @wingtip? Ok, the influence of reduced cd on stall behavior should be quite clear now. RC pilots normally don't like digging their models... Smiley Therefore we do not talk about teamwork performance of this TL series, just about possible application using one airfoil for wingdesign. The main attention during design phasis aimed for long laminar run on airfoil lower surface at high speed (cl=0.1 .. 0.0). This is the basis to achieve low airfoil drag at highspeed. Inspite of 2,41% camber TL54 reached this design goal. We have here an airfoil that provides a lot of lift (clmax) despite very low drag at low CL! The direct consequence is an extremely wide area of application!