Ansys extensive analysis of aircraft wing.

In this assignment, you will use FEA to model and analyse the structural behaviour of an aerospace wing and its 
main load-carrying element, the wing box. A wing box is a structural component that forms the main part of an 
aircraft wing. It consists of two spars (longitudinal beams) that run along the span of the wing and several ribs 
(transverse beams) that connect the spars and provide support for the skin (outer surface) of the wing. The wing 
box carries the aerodynamic loads generated by the lift and drag forces acting on the wing, as well as the fuel weight 
and the landing gear loads. 
The objective of this assignment is to use FEA to design and determine the stress distribution and deformation of 
the wing box under different loading scenarios and make sure that your design can withstand the applied load 
without any material yielding. You will learn how to create a mesh, apply boundary conditions and load conditions 
and how to interpret the results of the analysis. 
You will use ANSYS Mechanical as the FEA software for this assignment.  
The generic process to be followed is as follows: 
 Import initial wing geometry into Ansys Mechanical. The initial geometry (iges file) of the wing box can be 
downloaded from Drive link. Then you need to define the geometry dimensions of the wing parts. You should 
choose appropriate thicknesses for the skin, ribs, and spars so as no yielding occurs. (for this simply select 
planer element, add thickness and use mesh attribute to assign it to the imported geometry) 
 Generate a finite element mesh (FE mesh) of the wing using ANSYS Mechanical. Choose an appropriate 
element type, size, shape, and aspect ratio for the mesh. Explain how you ensured the quality of the mesh and 
how you verified it. 
 Define the boundary conditions for the FE mesh. The boundary conditions include the connections at the root 
of the wing, where it is attached to the fuselage, and any other prescribed displacements or rotations.  
 Apply the loading conditions to the FE mesh. The loading conditions include the aerodynamic lift and drag 
forces. You will simulate two loading cases: (1) wing-up and (2) wing-down. Wing-up loading occurs when 
the aircraft is in a positive g manoeuvre, such as a climb or a turn. Wing-down loading occurs when the aircraft 
is in a negative g manoeuvre, such as a dive or a roll.  To apply loads on leading edge, go to plot—lines (you 
would now be able to see and select lines/keypoints only) 
2 
Fem lab 
To calculate the load, use the following data of the two flight conditions: 
Loading case Lift coefficient Drag coefficient Angle of attack 
Wing-up 
Wing-down 
0.84 -0.3 
0.05 
0.02 
You can calculate the lift and drag forces acting on the wing box as follows: 
Lift force = Lift coefficient x Dynamic pressure x Wing area 
Drag force = Drag coefficient x Dynamic pressure x Wing area 
Dynamic pressure = 0.5 x Air density x Airspeed2 
You will use the following data for the air density and airspeed: 
Air density = 1.225 kg/m3 
Airspeed = 100 m/s (for roll nums ending in 2, 7 and 4) 
Airspeed = 10 m/s (for roll nums ending in 1, 6 and 3) 
Airspeed = 140 m/s (for roll nums ending in 5 and 0) 
Airspeed = 60 m/s (for roll nums ending in 8 and 9) 
Area 
Chord 
23.78312m 
2.73687m 
Span 
8° -3° 
9.43m 
You apply the lift and drag forces; an equivalent total load is applied to nodes located at the tip of the wing. 
 The material used is an Aluminium alloy 2024-T3 with the following material properties:  
Young's Modulus  
(GPa) 
Poisson Ratio 
74 GPa 
0.33 
Density 
(kg/m3) 
Yield Strength  
(MPa) 
2780 
345 MPa 
 Perform the FEA and obtain the stress and displacement distribution in the wing and identify any regions of 
high stress concentration or deformation. 
 Plot the stress (strain) and displacement distribution in the wing for two different aerodynamic load cases. The 
plot should be color-coded to show the regions of high and low stress in the wing. The plot should also include 
a legend, a title, and axis labels to make it clear and informative. The plot should be compared with the yield 
strength of the material used for the wing to check if the wing is safe or not.