Numerical Simulation of Fluid Dynamics and Combustion for Ram Accelerator Projectile/Obturator Interaction
Abstract
Computational fluid dynamics solutions of the Navier-Stokes equations have been applied to both nonreacting and reacting in-bore flowfields for a ram accelerator projectile launch system. In this system, a projectile is injected at supersonic velocity into a stationary tube filled with a pressurized mixture of hydrocarbon, oxidizer, and inert gases. After ignition, the shock system generated by the projectile can result in sustained combustion around and aft of the projectile. This energy release process, which travels with the projectile, also generates high pressures and imparts thrust to the projectile. Experimental observations indicate that the porous obturator may play a significant role in the initiation of combustion after projectile injection. Numerical simulations have been used to investigate the role of the obturator in both the 38mm and 120mm (bore diameter) systems. Fluid dynamics, Hypervelocity guns, Navier Stokes equations, Ramjet engines, Supersonic combustion, Reacting flows.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1993
- Accession Number
- ADA269715
Entities
People
- Michael J. Nusca
Organizations
- United States Army Research Laboratory