HI Everyone.(adsbygoogle = window.adsbygoogle || []).push({});

First of all, I'm not an aeronautical or mechanical engineer. I'm an electronics engineer but I'm currently doing a group project where I'm required to carry out a stability analysis on an aircraft that we've designed using the simulator software, X Plane.

I apologise in advance if any of these questions are stupid....

I know where the aircraft centre of gravity is but

How do I determine the Aerodynamic Centre of my aircraft?

I know that during steady flight, I must prove that all resultant moments acting around the centre of gravity should = 0, and

I've got Cm vs Alpha graphs for the tail airfoil (NACA 0009) and I'm in the process of trying to get the same graphs off X plane for the wing airfoils (Boeing Subsonic) but these will give me 2 completely seperate moment coefficients for 2 different airfoils.

How do I get the Moment Coefficient about the Centre of Gravity from these?

Any help would be very gratefully received.

Thanks

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# Static Stability of Aircraft designed in X Plane g

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