Please solve with MATLAB. Please wright code in a code-like format.

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: T_6 = 273 K, the resistance through each material: R_A = 0.1 K/W, R_B = 0.001 K/W, R_C = 0.07 K/W, R_D = 0.04 K/W and R_E = 0.3 K/W, and the heat transfer rate: q = 68.5 W. Determine the temperatures between each layer of material and the inner surface. q = (T, - T_2)/R_A q = (T_2 - T_3)/R_B q = (T_3 - T_4)/R_C q = (T_4 - T_5)/R_D q = (T_5 - T_6)/R_E