Lately I did add a coupling between MIAReX and Xfoil : MIAReX can handle Xfoil calculation. You can automatically generate polars file needed for non linear lifting line calculation.
You can also fill the wing surface with colors corresponding to local CP value. |
Here is a page about a program I wanted to have since a while : a program that compute polar for multi-airfoil wing.
The calculation method used is based on lifting line theory, généralised to non linear behaviour of airfoil section. It computes lift distribution along span, with induced angle for finite wing. Then the program do the sum of local lift Cl, induced and airfoil drag Cdi& Cdairf, and airfoil moment Cm, to get global coefficient Cl, CDI, CDairf, andCM.
This program is based on formula developed by James C. Sivells & Robert H. Neely
in NACA TN-1269 (1947) :
For a rectangular wing, the chord is constant
along span, hence Reynolds number. We may thinks that taking raw 2D data
for airfoil behaviour is a fairly good approximation.
This is not as a good approximation, since allong span
the induced angle changes, and then the airfoil local drag. Thanks MIAReX we
will evaluate the effect of this 3D phenomenon on the overall performance.
Here is the story of the "aerodynamic tuning" of a small Nimbus 4D model, that had strange behavior. MIAReX was used for wing pitching moment analysis.
MIAReX was used for illustrating www.cirrusstandard.org web site.
Matlab Optimisation toolbox is a very powerful set of numerical optimization routines. The output of Miarex calculation was redirected to those optimisation routines, for precise design cases.