Accession Number:

ADA297325

Title:

Shock Induced Detonation on Projectiles in Hypersonic Flows of Detonable Gas Mixtures.

Descriptive Note:

Final rept. 1 May 94-31 Apr 95,

Corporate Author:

TECHNION RESEARCH AND DEVELOPMENT FOUNDATION LTD HAIFA (ISRAEL)

Personal Author(s):

Report Date:

1995-06-30

Pagination or Media Count:

77.0

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 its 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

Subject Categories:

  • Ballistics
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE