MH 54


Direct link: MH 54
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.
MH 54
Family: Hepperle
Max thickness: 8.0% at x = 35.76% chord
Max camber: 0.6% at x = 37.73% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition

Notes:


Coordinates from TraCFoil.
Commercial use of the airfoil may be restricted by the designer's copyright.
Very low drag coefficient airfoil for high speed model aircraft

http://www.mh-aerotools.de/airfoils/mh54koo.htm

Thickness: 8.00%

Camber: 0.6%

The ideal Reynolds number is about 1.7M

Ideal chord length about c[m] = 92 / v[km/h].

Very low drag if you reach beyond Re=1.5M

Could also be of interest for F3D pylon racing models.