Abstract:
The research studies the original design of (ZAGIL) wing from aeroelasticity point of view by enhancing computational software, theoretical approach and experimental tests to define the structural problem that existed in the wing.
The presence of a high stress zone in wing skin, ribs, spar and trialing edge occurs at operating condition Mach number 0.6 and angle of attack 12 degree considered as a main structural problem in the original wing of (ZAGIL) aircraft.
ANSYS fluent software and experimental tests results have been used to validate the aerodynamic and structural results obtained by finite element modeling and post processing (FEMAP) software, and the graphs show good agreement for both, aerodynamic and structural results.
To satisfy the working operation condition for the redesigned wing, the redesigned wing skin is compacted with leading edge, trailing edge and spar by using extrusion technology to manufacture the wing without rips.
