AaBbCcDc AaBbCcD AaBbC AaBbCcl AaBbCcl 11 Normal! TNo Spac Healing 1 Heading 2 Heading 3 , ' |A-y. A- It, ea. La Font Paragraph ME303 Applied Numerical Methods Problem 2 Airplane wings are made of composite materials. A simple 1-D analysis of the heat transfer through 5 layers of the wing results in the following system of linear equations. You know the temperatures on the outer surfaces: Te 273 K, the resistance through each material RA-0.1 KW. Re-0.001 KW, Rc-0.07 KW. RD=0 04 KW and RF0.3 KW, and the heat transfer rate: q-68.5 W Determine the temperatures between each layer of material and the inner surface T. T. T. q (T-T)/R q=(T2-T3)/Ro Probiem3 ihrations in mechanical structures can be modeled using systems of springs and blocks. Consider the