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What is Nozzle Configurations for Missile Thrust Optimization about?

This study analyzes the aerodynamic performance of various nozzle configurations for missile propulsion systems using Computational Fluid Dynamics (CFD). It compares convergent-divergent, bell-shaped, and conical designs to identify the most efficient configuration for optimal thrust and specific impulse. The research includes a modified dual-bell nozzle simulation, revealing an Exit Mach number of 2.2, while noting that practical performance may vary due to several factors.

Author

Maha Rajan

Language

EN