INVESTIGATION OF HIGH-SPEED PARTICLE EROSION OF MELTING AERODYNAMIC SURFACES

Abstract

The impact of atmospheric moisture particles on ablating hypersonic bodies was studied experimentally and theoretically. Various factors involved in the simulation of impacts with atmospheric-moisture particles during re-entry are discussed. The phenomena was studied experimentally in a rocket exhaust jet using small solid and liquid particles to simulate atmospheric moisture. Factors which could not be simulated in the rocket-exhaust-jet tests were analyzed theoretically. The experimental data were correlated using a mechanism based on the dissipation of particle energy in the melt layer. The results were extrapolated to the conditions of atmospheric re-entry. The results indicate that the ablation rate on a nose cone following a 3000 NM trajectory increases by a factor of 2 during flight through a cloud as a result of impacts with fine ice particles or water droplets.

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Document Details

Document Type
Technical Report
Publication Date
Sep 15, 1959
Accession Number
AD0260428

Entities

People

  • E. W. Ungar

Organizations

  • Battelle Memorial Institute

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Combustion
  • Combustion Products
  • Computational Fluid Dynamics
  • Energy Transfer
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Heat Energy
  • Heat Transfer
  • Heat Transfer Coefficients
  • Materials Laboratories
  • Materials Science
  • Mechanical Properties
  • Rocket Engines
  • Test And Evaluation
  • Thermodynamics

Fields of Study

  • Environmental science
  • Physics

Readers

  • Aerosol Science/Aerosol Physics
  • Thermal Physics or Thermal Science.

Technology Areas

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