MID 107
New! Bulk download of polars in Excel format: MID%20107.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: MID 107
Family: Midic
Max thickness: 10.0% at x = 26.50% chord
Max camber: 4.0% at x = 56.02% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
XFOIL ncrit=9
NF
Notes:
Coordinates from TraCFoil.
Commercial use of the airfoil may be restricted by the designer's copyright.
This airfoil has thickness of 10%, and camber of 4%.
It is intended for all FF airplane models for low speed
with Re numbers from 40,000 and more.
Airfoil must have appropriate turbulators at the top and/or
bootom side to provide turbulent flow on up side from
30%c and on down side from 5%c. By some models, they
fly only with higher lift, turbulator on the bottom side is
not need. To make turbulators more effective at small Re
numbers, on the top side invigators after 50%c are
welcome.
Because of relative big thickness of 10% it is easy to
build models also with wing of high aspect ratio
to the conventional mode with wooden spars.
Drag coeficient CD at zero lift CL=0 is very small in
comparison with usualy airfoils wit high cambers, so
the model can be suitable for succesfull vertical launching.
Slobodan Midic
Novi Sad, Jan. 2010.
NeuralFoil data computed using Peter Sharpe's NeuralFoil: An airfoil aerodynamics analysis tool using physics-informed machine learning, 2023, GitHub repository: https://github.com/peterdsharpe/NeuralFoil. Version 0.3.1 xxxlarge