Hussain

Thank you very much. I really appreciate it!

Hello, I am conducting a structural analysis for a morphing wing, and I want to determine the aerodynamic loads on a specific section of the wing. So, my first question is : can I obtain the pressure distribution in the chordwise direction for a segment of the wing in XFLR5 (more like an extruded pressure distribution in the 2D analysis where I can export the Cp graph and extract the data and then calculate the forces)? My second question is how can I obtain the rolling moment due to asymmetric flap...