The discussion revolves around analyzing shear and moment lines from a free body diagram (FBD) involving distributed forces, specifically related to the load distribution on the half-wing of an airliner.
The discussion is ongoing, with participants seeking clarification on the problem statement and exploring different approaches to the analysis. Some guidance has been offered regarding the direction of analysis, but no consensus has been reached on the best method to proceed.
Participants note that the original poster's teacher suggested that starting from the wing root might be easier than the proposed method of starting from the wingtip, indicating a potential assumption about the preferred approach.
"Determine the functions for the Shear and Moment (“V & M”) lines and put these functions in a table. Choose x=0 at the wingtip, then start working from the wingtip to the wing root. Consequently use the right section of a separation. Create a complete FBD for each required separation."Lnewqban said:
