MID 103
New! Bulk download of polars in Excel format: MID%20103.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 103
Family: Midic
Max thickness: 7.0% at x = 19.90% chord
Max camber: 4.1% at x = 56.01% 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 7%, and camber of 4.1%.
It is intended for all free flite (FF) airplane models for low speed with Re numbers from 40,000 and more.
Airfoil must have appropriate turbulators at the top and/or
bottom side to provide turbulent flow on up side from
30% of chord and on down side from 5% of chord.
On some
models, they fly only with higher lift, turbulator on the bottom
side is not need, so the drag is lower.
To make turbulators
more effective at small Re numbers, on the top side invigators
after 50% of chord are welcome.
Because of relative thin thickness of 7% it must build wing
of a high aspect ratio in a modern high technology mode.
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.
The airfoil is suitable for all FAI FF classis of flying models:
F1ABCE....
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