Computed In-Flight Temperature Response of a 120-mm XM797 Gas Generator Training Round Nose Cap.

Abstract

A computational study is presented of the aerothermal response of an XM797 gas generator nosecap. The XM797 nosecap is a critical component in the design of a 1 2O-mm finned kinetic energy (KE) training round projectile. A propellant-filled chamber within the nosecap is designed so that aerodynamic heating ignites the propellant down range, initiating projectile breakup. The objective of this study is to provide the nosecap temperature response, which is necessary to design the chamber geometry. A model for the aerodynamic heat transfer is constructed using a numerical boundary-layer technique. The heat transfer model provides the necessary boundary conditions for a numerical heat conduction analysis, which computes the temperature response throughout the nosecap. Analysis is presented for (1) a 105-mm version of the nosecap for which previous results are available and (2) the 12O-mm version of the nosecap currently of interest.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1995
Accession Number
ADA302378

Entities

People

  • Bernard J. Guidos

Organizations

  • United States Army Research Laboratory

Tags

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Central Processing Units
  • Computational Fluid Dynamics
  • Energy
  • Fluid Dynamics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Layers
  • Materials
  • Nose Caps
  • Propellants
  • Training
  • Turbulent Flow
  • United States Military Academy

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Dynamics.
  • ballistics.