MH 53
New! Bulk download of polars in Excel format: MH%2053.xlsx
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.
DB Name: MH 53
Family: Hepperle
Max thickness: 9.4% at x = 39.72% chord
Max camber: 0.4% at x = 15.58% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
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/mh53koo.htm
Thickness: 9.43%
Camber: 0.4%
The ideal Reynolds number is about 1.8M.
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.