Project on Visualize the Shock Structures from a CD Nozzle

Abstract

The project titled “Visualize the Shock Structures from a CD Nozzle” focuses on the study and visualization of compressible flow phenomena occurring inside and outside a Convergent-Divergent (CD) nozzle under different pressure conditions. In high-speed aerodynamic applications, shock waves are formed due to sudden changes in pressure, temperature, and velocity when the flow reaches supersonic conditions. The objective of this project is to analyze the formation of normal and oblique shock structures in a CD nozzle using computational and visualization techniques. The study examines variations in Mach number, pressure ratio, density, and velocity distribution throughout the nozzle section. Different flow regimes such as subsonic flow, choked flow, over-expanded flow, under-expanded flow, and perfectly expanded flow are investigated to understand the behavior of shock waves. The project employs simulation tools and fluid dynamics principles to generate graphical representations of pressure contours, Mach contours, and shock patterns. The obtained results help in understanding the aerodynamic performance and efficiency of nozzles used in aerospace propulsion systems, jet engines, rockets, and supersonic applications. The visualization of shock structures provides better insight into compressible fluid flow behavior and contributes to the design optimization of high-speed propulsion devices.