External Flow Computations for a Finned 60MM Ramjet in Steady Supersonic Flight.
Abstract
The US Army Ballistic Research Laboratory (BRL) has participated in the development of the launch and flight technologies for a family of solid fuel ramjet (SFRU) projectiles. The ramjet is a tubular projectile which utilizes air ingested through the inlet to burn the solid fuel. When the combustion process ceases, the projectile becomes a high drag configuration. Several designs have been developed as potential tank gun training rounds (TGTR) for kinetic energy (KE) penetrators. This report documents a computational fluid dynamics study of the external aerodynamics of a finned 60mm solid-fuel ramjet in steady, supersonic, atmospheric flight. The main objective is to compute the external contribution to the pitch-plane aerodynamics using established in-house capabilities. Two space-marching finite-difference procedures are used to compute the external flow fields. Viscous flow results are generated using a thin-layer, parabolized Navier-Stokes technique; inviscid results are generated using an Euler solver. Results are shown for three configurations; Body-alone, body with original fins, and body with extended fins. The influence of initial marching conditions on the modeling of an inlet configuration is examined. A generalized scaling law is introduced which may improve the accuracy of future external space-marching flow computations for ramjets. Keywords: Fin-stabilized projectile; Supersonic flow; Wedge flow; Conical flow. (AW)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1989
- Accession Number
- ADA216998
Entities
People
- Bernard J. Guidos
Organizations
- Ballistic Research Laboratory