Determination of Stability and Control Derivatives using CFD
 

Dear all
I am working on a flight simulation project to earn my master degree with it, the aerodynamic part is focused on the determination of the stability and control derivatives of a Wing-body-tail configuration by two methods:

1- using a very known semi-empirical tool called "AAA" (Advanced Aircraft Analysis)
2- using the CFD methods (solidworks --> ICEM --> CFX)

I have searched a lot the forums and everywhere on the internet for some answers about the determination of statibility and control derivatives using CFD, but without luck.

I made a lot of run by changing alpha and beta angles and speed, I obtain a set of data

(CD,CY,CL,Cl, Cm and Cn functions of alpha and beta angles and speed)
my questions are:

1- Could we obtain by the CFD methods all the stability and control derivatives?
2- What is difference in capability between Fluent and CFX (about derivatives)?
3- Is "dynamic mesh" a necessary method to obtain some derivatives (like CLq, CLalphadot ...)
4- Where could i found a 3D tutorial about a "dynamic mesh"

I hope that this thread gives clear answers to obtain a complete set of stability and control derivatives, so please anyone who knows anything about the subject is welcome to participate...

hello pavillion
Did have u finished ur project?, cause i also took up same project.

Same thing! Help anyone