Design of CRMC Non-Adiabatic Supersonic Nozzle

In engineering systems like jet propulsion steam turbines gas turbines and jet engines nozzles are crucial parts. They increase the speed of fluid flow from subsonic to supersonic or hypersonic levels producing the required thrust under certain design and operating circumstances. The efficiency thrust and flow rate of the nozzle are determined by its shape and flow characteristics making its design and analysis essential to the optimization of a variety of engineering systems. In this work sophisticated propelling nozzles are designed and analysed with an emphasis on their form and flow characteristics. Nozzle length is taken into account along with the assumption of constant momentum rate and 1-D gas dynamic equations are used to examine these variables.The constant rate of momentum change (CRMC) hypothesis which incorporates frictional effects and heat addition is utilised to obtain consistent flow characteristics at any distance. The findings of the CRMC theory are validated using computational fluid dynamics (CFD) using ANSYS Workbench 2022R2 which reveals that under design conditions the numerical conclusions and the CRMC theory results are in agreement.