Parabolized Navier-Stokes Computation of Surface Heat Transfer Characteristics for Supersonic and Hypersonic KE Projectiles

Abstract

Perfect gas heat transfer characteristics are presented for two existing supersonic finned kinetic energy (KE) projectiles (M735 and M829) and for a conceptual hypersonic KE projectile configuration. The hypersonic configuration is obtained by replacing the fins of the M829 with a conical flare of varying sweep angle. A three-dimensional, viscous, parabolized Navier-stokes (PNS) computational technique is used to compute the perfect gas adiabatic wall temperatures and heat transfer rates in the velocity range 1.3 /sec to 4 km/sec (Mach number range about 4 to 12). The heat transfer characteristics provide a necessary boundary condition for subsequent heat conduction computations, which simulate the transient in-flight thermal response of projectile configurations. Computational fluid dynamics, Convection heat transfer, Aerodynamic heating, Supersonic flow, Turbulent flow.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1993
Accession Number
ADA268858

Entities

People

  • Bernard J. Guidos
  • Paul Weinacht

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Heating
  • Boundary Layer
  • Computational Fluid Dynamics
  • Energy
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Heat Transfer
  • Hydrodynamics
  • Mach Number
  • Mechanical Properties
  • Mechanics
  • Physics Laboratories
  • Three Dimensional
  • Turbulent Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow