Good morning,
I‘m studying the stability of an aircraft for a project at university. I have calculated the global coefficients (lift, drag and moment) on FLUENT. How can I calculate the characteristics of some part of the aircraft? For example, the drag coefficient of the horizontal tail.
Many thanks
At the rear of the fuselage of most aircraft one finds a horizontal stabilizer and an elevator. The stabilizer is a fixed wing section whose job is to provide stability for the aircraft, to keep it flying straight. The horizontal stabilizer prevents up-and-down, or pitching, motion of the aircraft nose .
You may refer to :
you could make as named selection from the design modular (or spaceclaim) from the start, then in monitors select and the required aerodynamic characteristics.
Rashid Yagoub Many thanks! I'm doing it with Designmodeler and it works.
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