Supersonic Nozzle Flow Separation and Shock Wave CFD Simulation

Delve into the complex world of supersonic nozzle flow with our CFD simulation focusing on flow separation and shock wave formation. This advanced tutorial is tailored for mechanical engineers working with high-speed fluid dynamics and propulsion systems.

Key areas covered:

Compressible flow modeling in supersonic regimes
Shock wave formation and propagation
Boundary layer separation in adverse pressure gradients
Nozzle performance under various operating conditions

Learn to set up high-fidelity compressible flow models, capture shock waves, and analyze flow separation phenomena in supersonic nozzles.

This simulation provides critical insights into:

Mach number distribution along the nozzle
Shock wave structure and location
Pressure and temperature variations across shocks
Boundary layer behavior and separation points
Impact of back pressure on nozzle flow characteristics

Applicable to aerospace propulsion, rocket engines, and high-speed aerodynamics.

By completing this module, you’ll gain a deep understanding of:

Supersonic flow physics in converging-diverging nozzles
Shock-boundary layer interactions
Flow separation mechanisms in supersonic regimes
Performance implications of off-design nozzle operation

Develop advanced skills in analyzing and optimizing supersonic nozzle designs, crucial for propulsion system development and high-speed flow applications in mechanical engineering.