MID 327 9%
New! Bulk download of polars in Excel format: MID%20327%209%25.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 327 9%
Family: Midic
Max thickness: 9.0% at x = 28.24% chord
Max camber: 2.4% at x = 45.80% 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.
The airfoil has thickness of 9% and camber of 2.4%.
It's intended for Re numbers from 80k up to 800k, so
it can be good for R/C Soaring models as for F3B/J or
similar.
As the drag CD at lift of CL=0-1 is relative small it's good for
task A Duration, excelent for task B Distance and very good
for task C Speed in Multi Task Thermal Soaring Gliders F3B.
Caracteristics of model can be controled using flaps or
flaperons, but only with small deflections, because airfoil regard
good caracteristics without any controle of trailing edge. With
positive deflection of flaps more than +5 degre (down) max.
lift increase but drag increase very strong so as a good brake.
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