Finite difference solution of transient radial heat conduction in a multi-layer composite hollow cylinder

Solution for transient radial heat conduction in a multi-layer composite hollow cylinder with convective heating on the inner surface and insulation on the outer has been obtained by the use of Crank Nicholson's Finite-Difference Implicit method. The result would be useful for calculating the temperature distributions in rocket nozzles involving composite structures. The difference solutions are found to be in close agreement with the exact solution for the limiting case of a single layer. It is found that 50 space intervals and an interval of 0.1 sec in time are appropriate and sufficient to give reasonably accurate results useful for engineering design. The execution time is also very small.