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- MIAReX 0.9 -
- -
- Méthode d'Intégration sur une Aile de Résultat eXpérimentaux & Xfoil -
- Integral Method over a Wing for eXperimental and Xfoil Results -
- -
- Matthieu Scherrer (matthieu.scherrer.04@supaero.org) (august 2004) -
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What is MIAReX ?
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This program computes the aerodynamic parameter for a finite wing, taking airfoils
effect into account.
The calculation method used is based on lifting line theory, generalised to non linear
behaviour of airfoil section. It computes induced angle and lift distribution along span,
for finite wings, according to airfoils data.
Then it plot local lift Cl, induced and airfoil drag Cdi& Cdairf, and airfoil
moment Cm, and sums them to get global coefficient Cl, CDI, CDairf, and CM.
It is programmed for Matlab 6.5
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How to use MIAReX ?
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You must first launch Matlab6.5. Once in the right directory, just call "Miarex" into
Matlab command window, and follow the intructions :
[1]. Project geometry & airfoils setup
[2]. Single alfa computations
[3]. Multiple alfa computations
[4]. Set calculation parameter
[0]. Exit Miarex
[1] and its sub-menus allows to create, edit and save wing geometry and data.
[2] computes and plot local and global aerodynamic parameters for a given angle of attack.
The output of the calculation is formated into a *.txt file : output/projectname.m2d
[3] is a polar driving program : it computes and plots aerodynamics parameter for a
serie of alphas.
The output of the calculation is formated into a *.txt file : output/projectname.pol
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History
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- August 2004
A much more user friendly interface is now available. Project are created, including wing
geometry and airfoils. Special thanks Jean-Luc for his help !
- April 2004
First release.
Available : single alpha and polar calculation.
This program is free software
This program is distributed in the hope that it will be useful,
but WITHOUT ANY WARRANTY, concerning either the results or the
use than can be done.