Hi everyone, I am currently working on a Coanda UAV and I am aware that there's no mathematical model to express the lifting effects of Coanda. It is more of a physical description of airflow movement. Correct me if im wrong! Thus, I am using the generic expression of lift to describe the lift forces generated by the UAV. (dynamic pressure*area*coefficient). However, I am also curious if the Kutta Joukowski theorem can be applied to the Coanda UAV. From what I know KJT is for rotating cylinders and airfoils where Kutta condition must be met at the trailing edge. Coanda UAV doesn't seem to fulfill the requirement for KJT at all. Thus, I am currently presuming that (L=rho*velocity*circulation factor) cannot be applied to Coanda UAV. Here's a view of my axis-symmetric model of the Coanda UAV. Air will flow from the wireframe immediately above the fuselage skin, on to the top surface of the fuselage and be directed downwards due to Coanda effect.