Design, Analysis and Simulation of a Rocket Nozzle

Hamza Ashraf*, Shuaib Salamat**, Ali Sarosh***Aerospace Engineering Dept. College of Aeronautical Engineering National University of Sciences and Technology Rawalpindi, Pakistan.** Associate Professor, Aerospace Engg Dept. College of Aeronautical Engineering National University of Sciences and Technology Rawalpindi, Pakistan.

A high-fidelity computational solution for design of minimum length nozzles (MLN) is

proposed. The solution is based on frozen-flow and equilibrium-flow conditions. The

proposed solution is derived on the basis of Method of Characteristics (MoC) for a

specific exit Mach number of the nozzle. A user-friendly graphical user interface is also

developed to compute key geometric and performance parameters for the MLN design.

The program can be used to design the ‘Percentage Rao’ and ‘Conical nozzles’ as well.

The output for the code also includes a 2-D graphical plot of the nozzle geometry. The

computed geometrical parameters of the nozzle can be exported for Computational

Fluid Dynamics (CFD) simulation and analysis. CFD simulations show that the designed

nozzle was able to meet the aerothermodynamics requirements desired of a MLN

design.