Hi everyone.

I'm working in a recreational proyect. I have used a CFD (Tornado) to calculate the stability derivatives of a small aircraft.

The point is, the CFD software provides me the stability derivatives in wind-axis (stability-axis) but I need them in body axis. do you know they way (or expression) to convert to those axes?

for example I want Cxu but I have Cxalpha and Cxbetha... How I get Cxu from Cxalpha and Cxbetha??? (and the others components Cxv Cxw Cxq Cxp Cxr Cyu... Czu... Clu... Cmu... Cnu...Cnr)

thank you