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

Subject Code: EGA230 Internal Code: D_AI_DDFD_HA

Computer Aided Engineering Assessment Answer

Task: 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 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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