How to correct dynamic stability of UAV fuselages?

I was trying to design a fuselage model of UAV with considering lift coefficient (CL), after this I analyzed stability of both wing on fuselage. First I did the individual analysis for wing and fuselage in which the result of main wing analysis is quite good but after adding fuselage the dynamic stability of the UAV was not perfect.

If any information might be lacking I would love to add details and I am onto sure if my question is reliable for this forum ,if so it would be great if you could suggest a specified forums where I can discuss with this issue.

Thanks in advance.