Solve for the isentropic nozzle geometry, based on the method of characteristics (MOC), and written in Matlab.
Input: area ratio - between exit and throat Set initial value on area ratio depending on combustion chamber pressure. Inputs:
- gamma : Specific heat ratio
- Ae_At : Area ratio of nozzle [Note: This is basically the diameter ratio and not the area ratio in the code!!]
References [1] MoC methodology from J.D. Anderson book on Compressible flow, Chap - 11 [2] Reference guide - http://mae-nas.eng.usu.edu/MAE_5540_Web/propulsion_systems/section8/section.8.1.pdf
A simpler version of the code has been uploaded to understand the stagnation pressure and temperature variation in the nozzle from throat to exit. The sample figure shows a dis-continuity near the throat and it can be neglected.