Shock Induced Detonation on Projectiles in Hypersonic Flows of Detonable Gas Mixtures.
Abstract
This Final Report presents the developments in the research program during the period of contract N6817l94C9O65, May 1, 1994 to April 31, 1995. During this period the following subjects were investigated: (A) CFD results on the External Propulsion Accelerator (EPA) projectile configurations. (B) An analytical study on the stability of hypersonic reacting flow at the stagnation region of a blunt body using Dynamical System Analysis. (C) The Use of the EPA for Scramjet Combustion Research. (D) The Use of the EPA for Hypersonic Aerodynamic Test Facility. (E) Analysis of the Initiation of Detonation on a Hypervelocity Projectile and it's Maximum Velocity in the EPA. (F) Preparations for testing at the Army Research Laboratories Ram Accelerator facility at Aberdeen, MD. The CFD calculations on the projectile configurations indicated a well established external combustion zone and reasonably large thrust. Analysis using energy balance considerations indicated that the maximum projectile velocity in the EPA is about 6 times the detonation speed while that for the Ram Accelerator is about 1.3 times the detonation speed of the mixture. Therefore, the EPA is capable to accelerate missile-projectile to beyond the escape velocity and can be considered also for single stage to orbit missions. (AN)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 30, 1995
- Accession Number
- ADA297325
Entities
People
- Josef Rom