EGA230: Aerofoil Section with possible spar location – Computer Aided Engineering Assessment Answer

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Subject Code: EGA230
D_AI_DDFD_HA
Computer Aided Engineering Assessment Answer
Task:
Aerospace Engineering AssignmentAerospace Engineering Assignment
Wingspan: 15m / 49.2ft
Wing area: 12.4sq.m / 133.5sq.ft
Empty Weight: 255kg / 562lb
Payload: 195kg / 430lb
Gross Weight: 450kg / 992lb
Wing Load: 36.92kg/sq.m / 7.43lb/sq.ft
Water Ballast: 0
Aspect ratio: 18.2
Airfoil: Eppler E 603
Minsink: 0.70 m/s / 2.3 fps / 1.36 kt
Engineering Assignment
Properties Carbon/Epoxy Composite Sheet Property
Units Value Coefficient of thermal expansion – Longitudinal x10-6 K-1  2.1
Compressive Strength – Longitudinal MPa  570
Compressive Strength – Transverse MPa  570
Density g.cm-3  1.6
Shear modulus – in-plane GPa 5
Shear strength – in-plane MPa 90
Tensile strength – Longitudinal MPa 600
Tensile strength – Transverse MPa 600
Ultimate Compressive Strain – Longitudinal % 0.8
Ultimate Compressive Strain – Transverse % 0.8
Ultimate Shear Strain – in-plane % 1.8
Ultimate Tensile Strain – Longitudinal % 0.85
Ultimate Tensile Strain – Transverse % 0.85
The volume fraction of fibers % 50
Young’s Modulus – Longitudinal GPa 70
Young’s Modulus – Transverse GPa 70
TASK:
• Build your Solidworks model incorporating parameterisation.
• Create a study
• Define loads and restraints
• Mesh the model (using curvature-based mesh)
• Perform a mesh dependency study
• Run your simulations for the selected design possibilities using appropriate mesh settings.
• The plot, compare and analyze the stresses and vertical displacements on the left top surface edge, along with the overall determined factors of safety.
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