I possess an Aerospace Engineering background, and work as a Aerospace structural analyst at a local firm. A portion of my job is dedicated to determining the critical conditions that the aircraft and its component can undergo, and then conduct Finite Element Analysis for those components under these limiting loading conditions. Before jumping onto the CFD team (to acquire the loads), I first have to make up my mind what conditions I reckon should return me critical loads acting on the aircraft.
I usually make use of V-N diagrams to deduce which are the most critical loadings on my civil aircraft, beyond which the structure is deemed to have failed. However, the V-N diagrams for an aircraft don't include the Sideslip effect. I am not a CFD specialist, so I don't know what would be the response of the aircraft (and its components) when subjected to wind at a certain sideslip angle.
Assume, I am currently working on the fuselage component of my civil aircraft, and want to obtain the most critical loads which can possibly act on it while in flight. So how would the sideslip play a role in this scenerio? What happens to the lift and drag values as the sideslip angle keeps on increasing gradually from 0 degrees to 90 degrees, in flight? What pattern would the lift and drag follow during this period? Should this pattern be the same for all components of the aircraft (like fuselage, wing, tail, etc) or it can be different?