ME4212 Assignment (1) on Aircraft Wing
Note: This assignment accounts for 30% of total assessment for ME4212. It should be an individual and independent effort by each student. Please show sample calculations, all assumptions and include any code or software used. Neatness will also count towards assessment.
Deadline: 5.00 PM FRIDAY 20 MARCH 2026. No extension will be entertained.
Please submit via Canvas.
Attn: Prof T.E. Tay, with your name and matric number clearly stated. Please entitle your file(s) as follows: Assign(1)MatrixNumberFULLNAME.pdf and .xls
(e.g. Assign(1)A0123007JAMESBOND.pdf)
Fig. 1 shows the internal structure of the wing of an all-aluminum alloy aircraft (not to scale). It consists of the main structure, a rear spar, an airleron and spanwise stringers (stringers not shown). You may assume the structure behind the rear spar (airleron) is ineffective in carrying stresses.
Figs. 2 and 3 show scaled drawings of the wing, viewed from the top and the cross-section at the wing root, respectively. Fig. 4 provides information on the dimensions of the flanges or stringers, which are riveted to the skin and spars. The skin is t mm thick throughout.
An equivalent lift PL = 400 N is applied to the wing as shown in Figs. 1, 2 and 3.
Determine the maximum bending and shear stresses at the wing root if t = 1.2 mm.
State all assumptions clearly and provide sample calculations in your report. Please also include your code or Excel sheet.
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